Design method of moon-earth space communication navigation constellation system based on mbse

Abstract

This invention discloses a design method for a lunar space communication and navigation constellation system based on MBSE. The method includes: constructing a system-level architecture model of the lunar space communication and navigation constellation to obtain the lunar communication and navigation constellation system; modeling the requirements of the lunar communication and navigation constellation system using SysML requirement diagrams to obtain performance index requirements for different users in different functional aspects; establishing parameterized orbital mechanics models and link transmission models based on the orbital types in the lunar space communication and navigation constellation; and constructing a target performance simulation model corresponding to the lunar communication and navigation constellation system using the performance index requirements, orbital mechanics model, and link transmission model. This invention utilizes the SysML modeling language to achieve a digital closed loop for the lunar space communication and navigation constellation from task requirement definition to system architecture design and simulation evaluation, enabling rapid iteration and dynamic expansion of system design, thereby significantly improving the efficiency of lunar communication and navigation constellation system design.

Description

Technical Field

[0001] This invention relates to the field of deep space exploration technology, and in particular to a design method for a lunar-Earth space communication and navigation constellation system based on MBSE. Background Technology

[0002] As lunar exploration missions gradually shift from short-term exploration to long-term deployments, communication and navigation infrastructure in the Earth-Moon space has become a crucial guarantee for the long-term operation of deep space exploration missions. Existing deep space exploration missions mainly rely on ground-based deep space tracking and control networks, but due to the geometric relationship between the Earth and the Moon, missions on the far side of the Moon and in the polar regions are often out of sight of ground stations. Furthermore, with the rapid increase in the number of deep space exploration missions, the existing deep space tracking and control network is insufficient to support the future demand for multiple parallel missions. Therefore, there is an urgent need to construct an Earth-Moon space communication and navigation constellation. Simultaneously, by utilizing the inter-satellite links established between satellites in the Earth-Moon space communication and navigation constellation to achieve autonomous orbit determination, the constellation can achieve autonomous operation, thereby providing continuous, stable, and reliable communication and navigation services to users in the Earth-Moon space. Faced with the complex dynamic environment of the Earth-Moon space and the diverse needs of different users, the configuration and system design of the Earth-Moon communication and navigation constellation require iterative iteration and optimization. Existing Earth-Moon space communication and navigation constellation designs are often based on document-based and static analysis systems engineering methods, lacking flexibility and global optimization capabilities, and unable to quickly adapt to changes in mission requirements. Summary of the Invention

[0003] This invention provides a design method for a lunar-Earth space communication and navigation constellation system based on MBSE, in order to solve the technical problems of existing system engineering methods based on documents and static analysis, which lack flexibility and global optimization capabilities and cannot quickly adapt to changes in mission requirements.

[0004] According to one aspect of the present invention, a design method for a lunar-Earth space communication and navigation constellation system based on MBSE is provided, comprising: A system-level architecture model of the Earth-Moon space communication and navigation constellation is constructed to obtain the Earth-Moon communication and navigation constellation system. The requirements of the Earth-Moon communication and navigation constellation system are modeled using SysML requirement diagrams to obtain the performance index requirements of different users in different functional aspects. Based on the orbit type in the Earth-Moon space communication and navigation constellation, a parameterized orbital mechanics model and a link transmission model are established. The target performance simulation model of the Earth-Moon communication and navigation constellation system is constructed based on the performance index requirements, the orbital mechanics model, and the link transmission model.

[0005] According to another aspect of the present invention, a design apparatus for a lunar-Earth space communication and navigation constellation system based on MBSE is provided, comprising: The system construction module is used to build the system-level architecture model of the Earth-Moon space communication and navigation constellation, resulting in the Earth-Moon communication and navigation constellation system; The requirements modeling module is used to model the requirements of the Earth-Moon communication and navigation constellation system using SysML requirements diagrams, and to obtain the performance index requirements of different users in different functional aspects. The transmission model construction module is used to establish a parameterized orbital mechanics model and link transmission model based on the orbital type in the Earth-Moon space communication and navigation constellation. The simulation model construction module is used to construct the target performance simulation model corresponding to the Earth-Moon communication and navigation constellation system based on the performance index requirements and the orbital mechanics model and link transmission model.

[0006] According to another aspect of the present invention, an electronic device is provided, the electronic device comprising: At least one processor; and A memory communicatively connected to the at least one processor; wherein, The memory stores a computer program that can be executed by the at least one processor, which enables the at least one processor to execute the design method of the Earth-Moon space communication and navigation constellation system based on MBSE as described in any embodiment of the present invention.

[0007] According to another aspect of the present invention, a computer-readable storage medium is provided, the computer-readable storage medium storing computer instructions for causing a processor to execute and implement the design method of the Earth-Moon space communication and navigation constellation system based on MBSE as described in any embodiment of the present invention.

[0008] According to another aspect of the present invention, a computer program product is provided, the computer program product comprising a computer program that, when executed by a processor, implements the design method of the Earth-Moon space communication and navigation constellation system based on MBSE as described in any embodiment of the present invention.

[0009] The technical solution of this invention involves constructing a system-level architecture model of the Earth-Moon space communication and navigation constellation to obtain the Earth-Moon communication and navigation constellation system; modeling the requirements of the Earth-Moon communication and navigation constellation system using SysML requirement diagrams to obtain performance index requirements for different users in different functional aspects; establishing parameterized orbital mechanics models and link transmission models based on the orbital types in the Earth-Moon space communication and navigation constellation; and constructing a target performance simulation model corresponding to the Earth-Moon communication and navigation constellation system using performance index requirements, orbital mechanics models, and link transmission models. This invention utilizes the SysML modeling language to achieve a digital closed loop for the Earth-Moon space communication and navigation constellation from task requirement definition to system architecture design and simulation evaluation. Furthermore, it supports rapid solution adjustment and automated verification under different task requirements, enabling rapid iteration and dynamic expansion of system design, thereby significantly improving the efficiency of Earth-Moon communication and navigation constellation system design.

[0010] It should be understood that the description in this section is not intended to identify key or essential features of the embodiments of the present invention, nor is it intended to limit the scope of the invention. Other features of the invention will become readily apparent from the following description. Attached Figure Description

[0011] To more clearly illustrate the technical solutions in the embodiments of the present invention, the accompanying drawings used in the description of the embodiments will be briefly introduced below. Obviously, the accompanying drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0012] Figure 1 This is a flowchart illustrating a design method for a lunar-Earth space communication and navigation constellation system based on MBSE, provided in an embodiment of the present invention. Figure 2 This is a flowchart of another design method for a lunar space communication and navigation constellation system based on MBSE provided in an embodiment of the present invention; Figure 3 This is a flowchart of another design method for a lunar space communication and navigation constellation system based on MBSE provided in this embodiment of the invention; Figure 4 This is a schematic diagram of the configuration of a lunar communication and navigation constellation provided in an embodiment of the present invention; Figure 5 This is an architecture diagram of a lunar communication and navigation constellation provided in an embodiment of the present invention; Figure 6 This is a mission requirement diagram of a lunar communication and navigation constellation provided in an embodiment of the present invention; Figure 7 This is a parameter diagram of a lunar communication and navigation constellation provided in an embodiment of the present invention; Figure 8 This is a schematic diagram of the structure of a design device for a lunar-Earth space communication and navigation constellation system based on MBSE, provided in an embodiment of the present invention. Figure 9 This is a structural block diagram of an electronic device provided in an embodiment of the present invention. Detailed Implementation

[0013] To enable those skilled in the art to better understand the present invention, the technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present invention. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort should fall within the scope of protection of the present invention.

[0014] It should be noted that the terms "first," "second," etc., in the specification, claims, and accompanying drawings of this invention are used to distinguish similar objects and are not necessarily used to describe a specific order or sequence. It should be understood that such data can be interchanged where appropriate so that embodiments of the invention described herein can be implemented in orders other than those illustrated or described herein. Furthermore, the terms "comprising" and "having," and any variations thereof, are intended to cover a non-exclusive inclusion; for example, a process, method, system, product, or apparatus that comprises a series of steps or units is not necessarily limited to those steps or units explicitly listed, but may include other steps or units not explicitly listed or inherent to such processes, methods, products, or apparatus.

[0015] In one embodiment, Figure 1 This is a flowchart illustrating a design method for a lunar-Earth space communication and navigation constellation system based on MBSE, provided in an embodiment of the present invention. This embodiment is applicable to the modeling of lunar-Earth space communication and navigation constellations. The method can be executed by an MBSE-based lunar-Earth space communication and navigation constellation system design device, which can be implemented in hardware and / or software and can be configured in an electronic device. Figure 1 As shown, the method includes: S110. Construct a system-level architecture model for the Earth-Moon space communication and navigation constellation to obtain the Earth-Moon communication and navigation constellation system.

[0016] In one example, the Earth-Moon space communication and navigation constellation is deployed in Earth-Moon space and is built on a Distant Retrograde Orbit (DRO). It is a satellite networking system that integrates communication, navigation, and orbit determination functions.

[0017] In one example, a system-level architecture model of the Earth-Moon communication and navigation constellation can be established. The system boundaries and main components, including the ground segment, space segment, lunar surface segment, and user segment, are defined using a SysML module definition graph, resulting in the Earth-Moon communication and navigation constellation system. The ground segment includes modules such as deep space tracking and control stations, data processing centers, and ground time reference centers; the space segment includes Earth orbit satellites, lunar orbit satellites, and Earth-Moon space orbit satellites (including libration orbit satellites and DRO orbit satellites); the lunar surface segment includes lunar surface data relay stations and lunar surface time reference centers; and the user segment includes Earth orbit users, Earth-Moon transfer orbit users, lunar orbit users, and lunar surface users.

[0018] S120. The requirements of the Earth-Moon communication and navigation constellation system are modeled using SysML requirement diagrams to obtain the performance index requirements of different users in different functional aspects.

[0019] In one example, the system requirements of the Earth-Moon communication and navigation constellation are modeled using a SysML requirements graph, clarifying the performance requirements for different users—Earth orbit users, Earth-Moon transfer orbit users, Lunar orbit users, and Lunar surface users—in the three core functions of communication, navigation, and timing. Communication performance indicators may include, but are not limited to, at least one of the following: downlink rate, uplink rate, and latency. Navigation performance indicators may include, but are not limited to, at least one of the following: position accuracy, velocity accuracy, time availability, and geometrical dilution of precision (GDOP). Timing performance indicators may include, but are not limited to, at least one of the following: timing accuracy and clock drift.

[0020] S130. Based on the orbital type in the Earth-Moon space communication and navigation constellation, establish a parameterized orbital mechanics model and link transmission model.

[0021] In one example, orbit type refers to the types of orbits that can be included in the Earth-Moon space communication and navigation constellation. For example, orbit types can include, but are not limited to, at least one of the following: Earth orbit, lunar orbit, libration orbit, and DRO orbit.

[0022] In one example, a parameterized orbital mechanics model and link transmission model can be established based on various orbital types in the Earth-Moon communication and navigation constellation, such as Earth orbit, Moon orbit, translational point orbit, and DRO orbit.

[0023] S140. Construct a target performance simulation model for the Earth-Moon communication and navigation constellation system by using performance index requirements, orbital mechanics model, and link transmission model.

[0024] In one example, the target performance simulation model refers to a performance simulation model that can output performance indicators that meet the performance requirements of different users in different functional aspects. In one embodiment, the target performance simulation model includes at least one of the following: an inter-satellite link data simulation model; a constellation autonomous orbit determination model; a user link simulation model; and a user performance simulation model.

[0025] In one example, SysML parametric graphs can be used to integrate key indicators such as link power budget and communication, navigation, and timing performance to establish an executable target performance simulation model. This model includes an inter-satellite link data simulation model, a constellation autonomous orbit determination model, a user link simulation model, and a user performance simulation model. This enables the overall optimization design of the Earth-Moon communication and navigation constellation, taking into account system performance indicators such as communication capability, navigation accuracy, and timing accuracy. This allows for a comprehensive trade-off analysis between design variables and system indicators, providing a quantitative decision-making basis for the design and optimization of the Earth-Moon communication and navigation constellation.

[0026] The technical solution of this embodiment obtains the Earth-Moon communication and navigation constellation system by constructing a system-level architecture model of the constellation; it models the requirements of the constellation system using SysML requirement diagrams to obtain the performance index requirements of different users in different functional aspects; it establishes parameterized orbital mechanics and link transmission models based on the orbital types in the constellation; and it constructs a target performance simulation model of the constellation system based on the performance index requirements, orbital mechanics model, and link transmission model. This invention utilizes the SysML modeling language to achieve a digital closed loop for the Earth-Moon communication and navigation constellation, from task requirement definition to system architecture design and simulation evaluation. Furthermore, it supports rapid solution adjustment and automated verification under different task requirements, enabling rapid iteration and dynamic expansion of system design, thereby significantly improving the efficiency of Earth-Moon communication and navigation constellation system design.

[0027] In one embodiment, Figure 2 This is a flowchart illustrating another design method for a lunar-Earth space communication and navigation constellation system based on MBSE, provided in this embodiment of the invention. This embodiment, based on the above embodiments, provides a detailed explanation of the construction process of the lunar-Earth communication and navigation constellation system, the modeling process of performance indicator requirements, and the construction process of the target performance simulation model. Figure 2 As shown, the method includes: S210. Obtain at least one of the following segments in the Earth-Moon space communication and navigation constellation: the ground segment, the space segment, the lunar segment, and the user segment.

[0028] In one example, the ground segment, space segment, lunar segment, and user segment are all major components of the Earth-Moon space communication and navigation constellation; the ground segment may include, but is not limited to, at least one of the following: deep space tracking and control stations, data processing centers, ground time reference centers, etc.; the space segment may include, but is not limited to, at least one of the following: Earth orbit satellites, lunar orbit satellites, Earth-Moon space orbit satellites (e.g., libration orbit satellites, DRO orbit satellites, etc.); the lunar segment may include, but is not limited to, at least one of the following: lunar data relay stations, lunar time reference centers, etc.; the user segment may include, but is not limited to, at least one of the following: Earth orbit users, Earth-Moon transfer orbit users, lunar orbit users, lunar surface users, etc.

[0029] S220. The SysML module is used to construct the modules contained in at least one of the ground segment, space segment, lunar segment and user segment, and the SysML module is used to define the graph and system boundary of the Earth-Moon space communication and navigation constellation to obtain the Earth-Moon communication and navigation constellation system.

[0030] In one example, a system-level architecture model of the Earth-Moon communication and navigation constellation is established. The system boundaries and main components, including the ground segment, space segment, lunar segment, and user segment, are defined using a SysML module definition graph. This yields the Earth-Moon communication and navigation constellation system.

[0031] S230. Obtain the communication, navigation and timing function requirements of different users in the Earth-Moon communication and navigation constellation system.

[0032] In one example, different users of the Earth-Moon communication and navigation constellation system may include, but are not limited to, at least one of the following: Earth orbit users (also known as Earth orbit satellite users), Earth-Moon transfer orbit users, lunar orbit users, lunar surface users, etc.; functional aspects may include, but are not limited to, at least one of the following: communication, navigation, and timing functions. It can be understood that users have different performance requirements for different functional aspects; among them, communication performance indicators may include, but are not limited to, at least one of the following: downlink rate, uplink rate, latency, etc.; navigation performance indicators may include, but are not limited to, at least one of the following: position accuracy, velocity accuracy, time availability, GDOP, etc.; timing performance indicators may include, but are not limited to, at least one of the following: timing accuracy (also known as user timing accuracy), clock drift (also known as clock drift control), etc.

[0033] S240. The requirements of different users in communication, navigation and timing functions are modeled using SysML requirement diagrams to obtain the performance index requirements of different users in different functions.

[0034] In one example, performance metric requirements refer to the performance metric requirements of different users for different functions. This can be understood as different users having different performance metric requirements for the same function.

[0035] For example, for users in Earth orbit, the performance requirements for communication include: downlink speed greater than or equal to 100 Mbps, uplink speed greater than or equal to 50 Mbps, and latency less than or equal to 0.2 s; the performance requirements for navigation include: position accuracy less than or equal to 10 meters (m), speed accuracy less than or equal to 0.1 m / s, and time availability greater than or equal to 99%; the performance requirements for timing include: timing accuracy less than or equal to 10 ns, and clock drift less than or equal to 1 ns. 10 -12 s / s.

[0036] For example, for users in the Earth-Moon transfer orbit, the performance requirements for communication include: downlink speed greater than or equal to 10 Mbps, uplink speed greater than or equal to 2 Mbps, and latency less than or equal to 1.3 s (i.e., round-trip latency less than or equal to 1.3 s); the performance requirements for navigation include: position accuracy less than or equal to 300 meters (m), speed accuracy less than or equal to 0.3 m / s, and time availability greater than or equal to 95%; the performance requirements for timing include: timing accuracy less than or equal to 20 ns, and clock drift less than or equal to 5 × 10⁻⁶. -12 s / s.

[0037] For example, for users in lunar orbit, the performance requirements for communication include: downlink speed greater than or equal to 20 Mbps, uplink speed greater than or equal to 5 Mbps, and latency less than or equal to 0.6 s; the performance requirements for navigation include: position accuracy less than or equal to 100 meters (m), velocity accuracy less than or equal to 0.2 m / s, and time availability greater than or equal to 98%; the performance requirements for timing include: timing accuracy less than or equal to 10 ns, and clock drift less than or equal to 1 × 10⁻⁶. -12 s / s.

[0038] For example, for lunar users, the performance requirements for communication include: downlink speed greater than or equal to 10 Mbps, uplink speed greater than or equal to 1 Mbps, and latency less than or equal to 1.3 s; the performance requirements for navigation include: position accuracy less than or equal to 30 meters (m), speed accuracy less than or equal to 0.1 m / s, time availability greater than or equal to 95%, and GDOP less than or equal to 10; the performance requirements for timing include: timing accuracy less than or equal to 100 ns, and clock drift less than or equal to 1 × 10⁻⁶. -11 s / s.

[0039] S250. Based on the orbital types in the Earth-Moon space communication and navigation constellation, establish a parameterized orbital mechanics model and link transmission model.

[0040] S260. At least some of the SysML parameters in the SysML parameter diagram associated with the orbital mechanics model and the link transmission model are used as input parameters and input into the initial performance simulation model corresponding to the Earth-Moon communication and navigation constellation system to obtain the corresponding output parameters.

[0041] In one example, the initial performance simulation model refers to the basic performance simulation model built for performance simulation, which can be understood as a basic performance simulation model that has not been optimized with actual data. In one example, key indicators such as link power budget and communication, navigation, and timing performance are first integrated using the SysML parameter diagram to establish an executable initial performance simulation model. The SysML parameters corresponding to different users are then used as input parameters and input into the corresponding initial performance simulation model to obtain the corresponding output parameters. In one example, the initial performance simulation model may include, but is not limited to, at least one of the following: inter-satellite link data simulation model; constellation autonomous orbit determination model; user link simulation model; user performance simulation model. In one embodiment, at least a portion of the SysML parameters in the SysML parameter diagram associated with the orbital mechanics model and the link transmission model are used as input parameters and input into the initial performance simulation model corresponding to the Earth-Moon communication and navigation constellation system to obtain the corresponding output parameters, including at least one of the following: Using at least one of the following parameters from the SysML parameter diagram associated with the orbital mechanics model and the link transmission model: translational point orbit parameters, Earth orbit parameters, lunar orbit parameters, satellite transmitting antenna parameters, satellite receiving antenna parameters, and link establishment parameters, input parameters into the inter-satellite link data simulation model corresponding to the Earth-Moon communication and navigation constellation system, at least one of the following parameters is obtained: inter-satellite link data, received power, and inter-satellite link delay between each satellite in the Earth-Moon communication and navigation constellation. At least one of the translational point orbit parameters, Earth orbit parameters, lunar orbit parameters, and inter-satellite link data from the SysML parameter diagram associated with the orbital mechanics model and the link transmission model is used as input parameters and input into the constellation autonomous orbit determination model corresponding to the Earth-Moon communication and navigation constellation system to obtain the constellation autonomous orbit determination accuracy. At least one of the following parameters from the SysML parameter diagram, which correlates the orbital mechanics model with the link transmission model: translational point orbital parameters, Earth orbital parameters, lunar orbital parameters, user parameters, satellite transmitting antenna parameters, satellite receiving antenna parameters, and satellite-user link establishment parameters, is used as input parameters and input into the user link simulation model corresponding to the Earth-Moon communication and navigation constellation system. This yields at least one of the following parameters: link data between each communication and navigation satellite and the user in the Earth-Moon communication and navigation constellation, user received power, and user link delay. By associating the orbital mechanics model with the link transmission model, at least some parameters from the SysML parameter diagram are input into the user performance simulation model to obtain the communication and navigation performance of the Earth-Moon communication and navigation constellation for the user.

[0042] In one embodiment, the translational point orbital parameters include: translational point number, orbital type, number of satellites, plane amplitude, vertical amplitude, and phase; Earth orbital parameters include: total number of satellites in Earth orbit, number of Earth orbital planes, relative phase parameters, orbital altitude, inclination, and eccentricity; Lunar orbital parameters include: the total number of satellites orbiting the Moon, the number of lunar orbital planes, relative phase parameters, orbital altitude, inclination, and eccentricity; Satellite transmitting antenna parameters include: transmit power, transmitter antenna gain, and wavelength; Satellite receiving antenna parameters include: receiver antenna gain; Link establishment parameters include: link establishment frequency and beam angle; User parameters include: user satellite orbital parameters or position and velocity.

[0043] In one example, at least one of the following parameters from the SysML parameter diagram associated with the orbital dynamics model and the link transmission model (e.g., translational point orbital parameters, orbital type, number of satellites, plane amplitude, vertical amplitude, and phase), Earth orbital parameters (e.g., total number of Earth orbit satellites, number of Earth orbital planes, relative phase parameters, orbital altitude, inclination, and eccentricity), lunar orbital parameters (e.g., total number of lunar orbit satellites, number of lunar orbital planes, relative phase parameters, orbital altitude, inclination, and eccentricity), satellite transmitting antenna parameters (e.g., transmit power, transmitter antenna gain, and wavelength), satellite receiving antenna parameters (e.g., receiver antenna gain), and link establishment parameters (e.g., link establishment frequency and beam angle) can be input into the inter-satellite link data simulation model corresponding to the Earth-Moon communication and navigation constellation system. This yields at least one of the following: inter-satellite link data, received power, and link delay between satellites in the Earth-Moon communication and navigation constellation. Here, inter-satellite link data refers to ranging data between satellites; the satellite's received power is determined by transmit power, transmitter antenna gain, wavelength, receiver antenna gain, transmission distance, and additional losses.

[0044] In one example, at least one of the following parameters is used as input parameters: translational point orbital parameters (e.g., translational point number, orbital type, number of satellites, plane amplitude, vertical amplitude, and phase), Earth orbital parameters (e.g., total number of Earth orbit satellites, number of Earth orbital planes, relative phase parameters, orbital altitude, inclination, and eccentricity), lunar orbital parameters (e.g., total number of lunar orbit satellites, number of lunar orbital planes, relative phase parameters, orbital altitude, inclination, and eccentricity), and inter-satellite link data. This input is fed into the constellation autonomous orbit determination model corresponding to the Earth-Moon communication and navigation constellation system to obtain the constellation autonomous orbit determination accuracy (e.g., position accuracy and velocity accuracy).

[0045] In one example, at least one of the following parameters from the SysML parameter diagram associated with the orbital mechanics model and the link transmission model—such as translational point orbital parameters (e.g., translational point number, orbital type, number of satellites, plane amplitude, vertical amplitude, and phase), Earth orbital parameters (e.g., total number of Earth orbit satellites, number of Earth orbital planes, relative phase parameters, orbital altitude, inclination, and eccentricity), lunar orbital parameters (e.g., total number of lunar orbit satellites, number of lunar orbital planes, relative phase parameters, orbital altitude, inclination, and eccentricity), user parameters (e.g., user satellite orbital parameters or position and velocity), satellite transmitting antenna parameters (e.g., transmit power, transmitter antenna gain, and wavelength), satellite receiving antenna parameters (e.g., receiver antenna gain), and satellite-user link establishment parameters (e.g., link establishment frequency and beam angle)—is input to the user link simulation model corresponding to the Earth-Moon communication and navigation constellation system. This yields at least one of the following: link data between each communication and navigation satellite and the user in the Earth-Moon communication and navigation constellation, user received power, and user link delay.

[0046] In one example, at least some parameters from the SysML parametric diagram, which associates the orbital mechanics model with the link transmission model, are input into the user performance simulation model to obtain the communication and navigation performance of the Earth-Moon communication and navigation constellation for the user. In another example, the user performance simulation model can be used to evaluate the communication and navigation performance of the Earth-Moon communication and navigation constellation for the user, including communication capability, navigation accuracy, and timing accuracy. For lunar users, navigation accuracy is evaluated by GDOP; for other Earth-Moon space orbit users, navigation accuracy is evaluated by orbit determination accuracy.

[0047] S270. If the output parameters meet the performance requirements, the performance simulation model corresponding to the output parameters meeting the performance requirements shall be used as the target performance simulation model.

[0048] In one example, if the output parameters meet the performance requirements of the corresponding user for the corresponding function, then the performance simulation model corresponding to the output parameters meeting the performance requirements can be directly used as the target performance simulation model. This can be understood as follows: if the output parameters of the initial performance simulation model meet the performance requirements, then the initial performance simulation model can be directly used as the target performance simulation model.

[0049] S280. If the output parameters do not meet the performance requirements, the input parameters are dynamically adjusted, and the adjusted input parameters are input into the latest performance simulation model corresponding to the Earth-Moon communication and navigation constellation system until the corresponding performance requirements are met, thus obtaining the target performance simulation model.

[0050] In one example, if the output parameters do not meet the performance requirements of the corresponding user in the corresponding function, the corresponding input parameters can be dynamically adjusted, and the adjusted input parameters can be input into the latest performance simulation model of the Earth-Moon communication and navigation constellation system until the corresponding performance requirements are met, thus obtaining the target performance simulation model.

[0051] In one embodiment, Figure 3 This is a flowchart illustrating another design method for a Moon-Earth space communication and navigation constellation system based on MBSE, provided in this embodiment of the invention. This embodiment, based on the above embodiments and as a preferred embodiment, provides a detailed explanation of the design process for a Moon-Earth space communication and navigation constellation system based on MBSE. Figure 3 As shown, the design method of the Earth-Moon space communication and navigation constellation system based on MBSE in this embodiment includes the following steps: S310. Establish a system-level architecture model for the Earth-Moon communication and navigation constellation, and define the system boundaries and main components through a SysML module definition diagram.

[0052] Figure 4 This is a schematic diagram of the configuration of a lunar communication and navigation constellation provided in an embodiment of the present invention. Figure 5 This is an architecture diagram of a lunar communication and navigation constellation provided in an embodiment of the present invention. First, the following is established: Figure 4 The system-level architecture model of the Earth-Moon communication and navigation constellation shown uses a SysML module definition diagram to define the system boundaries and main components, including the ground segment, space segment, lunar surface segment, and user segment, resulting in the following: Figure 5 The diagram shows the Earth-Moon communication and navigation constellation system. The ground segment includes modules such as deep space tracking and control stations, a data processing center, and a ground time reference center. The space segment includes Earth orbit satellites, lunar orbit satellites, and Earth-Moon space orbit satellites (including libration orbit satellites and DRO orbit satellites). The lunar surface segment includes lunar surface data relay stations and a lunar surface time reference center. The user segment includes Earth orbit users, Earth-Moon transfer orbit users, lunar orbit users, and lunar surface users.

[0053] In such Figure 4 The Earth-Moon communication and navigation constellation shown may include Low Earth Orbit (LEO), Medium Earth Orbit (MEO), Geostationary Earth Orbit (GEO), Near-Rectilinear Halo Orbit (NRHO), and DRO. L1, L2, L3, L4, and L5 are the five Lagrange points in Earth-Moon space.

[0054] S320: The system requirements of the Earth-Moon communication and navigation constellation are modeled using SysML requirement diagrams to clarify the performance indicator requirements of different users in the three core functions of communication, navigation and timing.

[0055] Figure 6 This invention provides a mission requirement diagram for a lunar communication and navigation constellation. The system requirements of the constellation are modeled using a SysML requirement diagram, clearly defining the performance indicator requirements for different users, such as Earth orbit users, Earth-Moon transfer orbit users, lunar orbit users, and lunar surface users, in the three core functions of communication, navigation, and timing. Figure 6 As shown, communication performance indicators may include, but are not limited to, at least one of the following: downlink rate, uplink rate, latency, etc. Navigation performance indicators may include, but are not limited to, at least one of the following: position accuracy, speed accuracy, time availability, GDOP, etc. Timing performance indicators may include, but are not limited to, at least one of the following: user timing accuracy, clock drift control, etc. Among these, `id` and `text` are two core attributes of the requirement element. `id` is used to represent a unique identifier for the requirement; it is automatically generated, and different requirements correspond to different `id`s. `text` is used to represent the specific content description of the requirement.

[0056] S330, combining multiple orbit types such as Earth orbit, lunar orbit, translational orbit, and DRO orbit, establishes a parameterized orbital dynamics and link transmission model.

[0057] Based on various orbit types in the Earth-Moon communication and navigation constellation, including Earth orbit, Moon orbit, translational orbit, and DRO orbit, a parameterized orbital mechanics model and link transmission model are established. Translational orbits are described using amplitude and phase. Taking the Lissajous orbit as an example, it is represented as... ; in, These are the three-dimensional position coordinates. Represents time, These represent the plane and vertical amplitudes, respectively. These are the phase parameters in the planar and vertical directions, respectively. The frequency parameters for the periodic orbital motion in the planar and vertical directions are respectively. ; For proportional parameters, ; in, . The masses of the Earth and the Moon are respectively. These represent the distances of the satellites to the Earth and the Moon, respectively. The Walker constellation, representing the Earth and Moon's orbits, is described using parameters such as N / P / F. N is the total number of satellites in the constellation, P is the number of orbital planes, and F is the relative phase parameter between satellites in adjacent orbits. The right ascension of the ascending node of the satellites in the constellation is also shown. and phase for: ; ; in, Indicates the track surface number. The satellites in this orbital plane are numbered. and These are the right ascension of the ascending node corresponding to the first orbital plane and the phase of the first satellite in that orbital plane, respectively.

[0058] S340 integrates parameters and indicators such as orbital parameters, communication, navigation, and timing performance through SysML parametric graphs to form an executable target performance simulation model.

[0059] Figure 7 This is a parameter diagram of a lunar communication and navigation constellation provided in an embodiment of the present invention. For example... Figure 7 As shown, by integrating key indicators such as link power budget and communication, navigation, and timing performance using SysML parametric diagrams, an executable performance simulation model is established. This model includes an inter-satellite link data simulation model (also known as an inter-satellite link data simulation module), a constellation autonomous orbit determination model (also known as a constellation autonomous orbit determination module), a user link simulation model (also known as a user link simulation module), and a user performance simulation model (also known as a user performance simulation module). This enables the overall optimization design of the Earth-Moon communication and navigation constellation, taking into account system performance indicators such as communication capability, navigation accuracy, and timing accuracy. It achieves a comprehensive trade-off analysis between design variables and system indicators, providing a quantitative decision-making basis for the design and optimization of the Earth-Moon communication and navigation constellation. Figure 7 As shown, the communication capabilities of Earth orbit users, Earth-Moon transfer orbit users, lunar orbit users, and lunar surface users can all be characterized by at least one of the following indicators: uplink rate, downlink rate, and latency.

[0060] User navigation in Earth orbit, user navigation in Earth-Moon transfer orbit, autonomous orbit determination and navigation of constellations, and user navigation in lunar orbit can all be characterized by at least one of the following indicators: position accuracy, velocity accuracy, and time availability; user navigation on the lunar surface can be characterized by at least one of the following indicators: position accuracy, velocity accuracy, GDOP, and time availability.

[0061] User time synchronization in Earth orbit, lunar orbit, lunar surface, and Earth-Moon transfer orbit can all be characterized by at least one of the indicators of user time synchronization accuracy and clock drift control.

[0062] User parameters can include position velocities in different directions (e.g., position velocities in the directions corresponding to the x, y, and z axes).

[0063] Step 1: Set the input parameters according to the parameter diagram, and use the inter-satellite link simulation model to call an external simulation program to generate inter-satellite link measurement simulation data. The input is the constellation orbit parameters, including the translation point orbit parameters: translation point number. Orbit type, number of satellites, plane amplitude and vertical amplitude phase Earth orbit parameters: Total number of satellites in Earth orbit Earth orbital plane number relative phase parameters orbital altitude ,inclination eccentricity Lunar orbital parameters: Total number of satellites orbiting the Moon Number of lunar orbital planes relative phase parameters orbital altitude ,inclination eccentricity Satellite transmitting antenna parameters, including transmission power. Transmitter antenna gain , Wavelength; satellite receiving antenna parameters, including receiver antenna gain. Chain establishment parameters, including chain establishment frequency. Beam angle Outputs inter-satellite link data between satellites in the Earth-Moon communication and navigation constellation, including satellite receiving power (i.e., the receiving power of the communication and navigation satellites) and inter-satellite link latency. The inter-satellite link data consists of ranging data between satellites, expressed as... ,in, The time of satellite 1 signal transmission. The time of satellite 2 signal reception. The position vector at the time of satellite 2 signal reception. The position vector at the moment when satellite 1 transmits the signal can be obtained by converting the corresponding translational orbit parameters, Earth orbit parameters, or lunar orbit parameters. At the speed of light, The clock errors of the onboard atomic clocks for Satellite 1 and Satellite 2 are respectively. For observation noise. Inter-satellite received power is expressed as: ; in, For received power, For transmission power, For transmitter antenna gain, For receiver antenna gain, For wavelength, For transmission distance, This is due to additional losses caused by atmospheric conditions, rain attenuation, etc.

[0064] Step 2: Set the input parameters according to the parameter diagram, and evaluate the autonomous orbit determination accuracy of the Earth-Moon communication and navigation constellation using the constellation autonomous orbit determination model. The input consists of initial values ​​for the constellation orbit parameters, including the translation point orbit parameters: translation point number. Orbit type, number of satellites, plane amplitude and vertical amplitude phase Earth orbit parameters: Total number of satellites in Earth orbit Earth orbital plane number relative phase parameters orbital altitude ,inclination eccentricity Lunar orbital parameters: Total number of satellites orbiting the Moon Number of lunar orbital planes relative phase parameters orbital altitude ,inclination eccentricity The inter-satellite link simulation module generates inter-satellite link data; the output is the constellation's autonomous orbit determination accuracy, including position and velocity accuracy. During the autonomous orbit determination process, the satellite state variables to be estimated are... The superscript indicates the satellite number. For satellite The state vector, and These are the satellite's position and velocity vectors, respectively. Clock error vector. ,in, The difference in clock offset parameters between satellite 1 and satellite 2. This represents the difference in frequency offset parameters between satellite 1 and satellite 2. This represents the difference in clock aging rates between Satellite 1 and Satellite 2. The initial guess value of the satellite's state vector is obtained by converting the input orbital parameters. Initial guess of the clock error vector The deviation between the initial guess and the actual value is denoted as . and The autonomous orbit determination equation is: ; in, , It is a 12-row, 1-column observation matrix. for The transpose of the matrix, and To observe the residuals, , From time At the time The state transition matrix, ; This represents the initial guess value of the satellite state variable to be estimated. This represents the initial guess of the clock error; This indicates the deviation between the actual and estimated values ​​of satellite state variables. This indicates the deviation between the actual and estimated values ​​of the satellite clock error.

[0065] residual The observation matrix is residual The observation matrix is .

[0066] in, , ; Let be the state vector of satellite 1. This is the state vector of satellite 2; The virtual distance 1 is the observed value obtained by adding the two one-way ranging data obtained from the i-th observation and eliminating the satellite clock error. The virtual distance 2 is the observed value obtained by subtracting the satellite orbit error from the two one-way ranging data obtained from the i-th observation. This is the difference between the observed value of virtual distance 1 and the theoretically calculated value of virtual distance 1. This is the difference between the observed value and the theoretical calculated value of virtual distance 2. For observations with a virtual distance of 1, This is the theoretical calculated value of the virtual distance 1. For the observation value of virtual distance 2, This is the theoretically calculated value for the virtual distance 2; It is a zero matrix with 1 row and 3 columns.

[0067] Step 3: Set the input parameters according to the parameter diagram, and use the user link simulation model to call an external simulation program to generate link measurement simulation data between the communication and navigation satellites and the user. The input is the constellation orbit parameters, including the translation point orbit parameters: translation point number. Orbit type, number of satellites, plane amplitude and vertical amplitude phase Earth orbit parameters: Total number of satellites in Earth orbit Earth orbital plane number relative phase parameters orbital altitude ,inclination eccentricity Lunar orbital parameters: Total number of satellites orbiting the Moon Number of lunar orbital planes relative phase parameters orbital altitude ,inclination eccentricity User parameters: User satellite orbital parameters or position velocity ,in, For the semi-major axis of the user star's orbit, For the orbital eccentricity of the user satellite, For the orbital inclination of the user satellite, The right ascension of the ascending node of the user star, The perigee argument of the user satellite. The true nearest angle for the user star; Let X be the position coordinates of the user satellite in the x-direction. Here are the position coordinates of the user satellite in the y-direction. Let be the position coordinates of the user satellite in the z-direction. Let be the magnitude of the user satellite's velocity in the x-direction. Let be the magnitude of the user satellite's velocity in the y-direction. The magnitude of the user satellite's velocity in the z-direction; satellite transmitting antenna parameters, including transmit power. Transmitter antenna gain , Wavelength; user receiver antenna parameters, including user receiver antenna gain. Satellite-user link establishment parameters, including satellite-user link establishment frequency. Satellite-user link establishment beam angle Outputs link data between users of the Earth-Moon communication and navigation constellation, including user received power and user link latency.

[0068] Step 4: Set the input parameters according to the parameter diagram, and use the user performance simulation model to evaluate the communication and navigation performance of the Earth-Moon communication and navigation constellation for users, including communication capability, navigation accuracy, and timing accuracy. For lunar surface users, navigation accuracy is evaluated by the geometrical precision factor (GDOP); for other Earth-Moon space orbit users, navigation accuracy is evaluated by orbit determination accuracy. GDOP = , Where G is an n x 4 matrix, To communicate from the user The direction vector of each navigation satellite To communicate from the user The direction vector of the navigation satellite on the X-axis, To communicate from the user The direction vector of the navigation satellite on the Y-axis, To communicate from the user The direction vector of each navigation satellite along the Z-axis; It refers to The sum of the elements on the main diagonal of this matrix, i.e. The trace of this matrix. User satellite orbit determination uses the following formula: , in, for Estimated value at any time The Kalman gain matrix is... for The observation residuals at time t, for The covariance matrix at time t, for The predicted covariance matrix at time 10:00. , From Time's up The state transition matrix at time t, From Time's up State transition matrix at time 1 The transpose of . , The equation for the link data observation between communication and navigation satellites and users.

[0069] In one embodiment, Figure 8 This is a schematic diagram of the structure of a design device for a lunar-Earth space communication and navigation constellation system based on MBSE, provided in an embodiment of the present invention. Figure 8 As shown, the device includes: a system construction module 810, a requirement modeling module 820, a transmission model construction module 830, and a simulation model construction module 840.

[0070] System construction module 810 is used to construct the system-level architecture model of the Earth-Moon space communication and navigation constellation, and obtain the Earth-Moon communication and navigation constellation system; The requirement modeling module 820 is used to model the requirements of the Earth-Moon communication and navigation constellation system using SysML requirement diagrams, and to obtain the performance index requirements of different users in different functional aspects. The transmission model construction module 830 is used to establish a parameterized orbital mechanics model and link transmission model based on the orbital type in the Earth-Moon space communication and navigation constellation. The simulation model building module 840 is used to construct the target performance simulation model of the Earth-Moon communication and navigation constellation system by using performance index requirements, orbital mechanics model and link transmission model.

[0071] In one embodiment, the system construction module 810 includes: The acquisition unit is used to acquire at least one of the ground segment, space segment, lunar segment, and user segment in the Earth-Moon space communication and navigation constellation. The system construction unit is used to construct the various modules contained in at least one of the ground segment, space segment, lunar segment and user segment through the SysML module, and to define the graph and system boundary of the Earth-Moon space communication and navigation constellation through the SysML module, so as to obtain the Earth-Moon communication and navigation constellation system.

[0072] In one embodiment, the requirement modeling module 820 includes: The requirement acquisition unit is used to acquire the requirements of different users in the Earth-Moon communication and navigation constellation system for communication, navigation and timing functions; The requirement building unit is used to model the requirements of different users in communication, navigation and timing functions using SysML requirement diagrams, and obtain the performance index requirements of different users in different functions.

[0073] In one embodiment, the simulation model construction module 840 includes: The parameter output unit is used to input at least some of the SysML parameters in the SysML parameter diagram that associates the orbital mechanics model with the link transmission model into the initial performance simulation model corresponding to the Earth-Moon communication and navigation constellation system, and obtain the corresponding output parameters. The model building unit is used to take the performance simulation model corresponding to the output parameters meeting the performance index requirements as the target performance simulation model, provided that the output parameters meet the performance index requirements. The model building unit is also used to dynamically adjust the input parameters when the output parameters do not meet the performance requirements, and input the adjusted input parameters into the latest performance simulation model corresponding to the Earth-Moon communication and navigation constellation system until the corresponding performance requirements are met, thus obtaining the target performance simulation model.

[0074] In one embodiment, the performance simulation model includes at least one of the following: Inter-satellite link data simulation model; constellation autonomous orbit determination model; user link simulation model; user performance simulation model.

[0075] In one embodiment, the parameter output unit is specifically used for at least one of the following: Using at least one of the following parameters from the SysML parameter diagram—translational point orbit parameters, Earth orbit parameters, lunar orbit parameters, satellite transmitting antenna parameters, satellite receiving antenna parameters, and link establishment parameters—as input parameters, the inter-satellite link data simulation model corresponding to the Earth-Moon communication and navigation constellation system is input to the Earth-Moon communication and navigation constellation system to obtain at least one of the following: inter-satellite link data, received power, and link delay between satellites in the Earth-Moon communication and navigation constellation. At least one of the translational point orbit parameters, Earth orbit parameters, lunar orbit parameters, and inter-satellite link data from the SysML parameter diagram associated with the orbital mechanics model and the link transmission model is used as input parameters and input into the constellation autonomous orbit determination model corresponding to the Earth-Moon communication and navigation constellation system to obtain the constellation autonomous orbit determination accuracy. At least one of the following parameters from the SysML parameter diagram, which correlates the orbital mechanics model with the link transmission model: translational point orbital parameters, Earth orbital parameters, lunar orbital parameters, user parameters, satellite transmitting antenna parameters, satellite receiving antenna parameters, and satellite-user link establishment parameters, is used as input parameters and input into the user link simulation model corresponding to the Earth-Moon communication and navigation constellation system. This yields at least one of the following parameters: link data between each communication and navigation satellite and the user in the Earth-Moon communication and navigation constellation, user received power, and user link delay. By associating the orbital mechanics model with the link transmission model, at least some parameters from the SysML parameter diagram are input into the user performance simulation model to obtain the communication and navigation performance of the Earth-Moon communication and navigation constellation for the user.

[0076] In one embodiment, the translational point orbital parameters include: translational point number, orbital type, number of satellites, plane amplitude, vertical amplitude, and phase; Earth orbital parameters include: total number of satellites in Earth orbit, number of Earth orbital planes, relative phase parameters, orbital altitude, inclination, and eccentricity; Lunar orbital parameters include: the total number of satellites orbiting the Moon, the number of lunar orbital planes, relative phase parameters, orbital altitude, inclination, and eccentricity; Satellite transmitting antenna parameters include: transmit power, transmitter antenna gain, and wavelength; Satellite receiving antenna parameters include: receiver antenna gain; Link establishment parameters include: link establishment frequency and beam angle; User parameters include: user satellite orbital parameters or position and velocity.

[0077] The MBSE-based Earth-Moon space communication and navigation constellation system design device provided in this embodiment of the invention can execute the MBSE-based Earth-Moon space communication and navigation constellation system design method provided in any embodiment of the invention, and has the corresponding functional modules and beneficial effects of the method execution.

[0078] In one embodiment, Figure 9 This is a structural block diagram of an electronic device provided in an embodiment of the present invention, such as... Figure 9 The diagram illustrates a schematic representation of an electronic device 10 that can be used to implement embodiments of the present invention. The electronic device is intended to represent various forms of digital computers, such as laptop computers, desktop computers, workstations, personal digital assistants, servers, blade servers, mainframe computers, and other suitable computers. The electronic device can also represent various forms of mobile devices, such as personal digital processors, cellular phones, smartphones, wearable devices (e.g., helmets, glasses, watches, etc.), and other similar computing devices. The components shown herein, their connections and relationships, and their functions are merely illustrative and are not intended to limit the implementation of the invention described and / or claimed herein.

[0079] like Figure 9 As shown, the electronic device 10 includes at least one processor 11 and a memory, such as a read-only memory (ROM) 12 or a random access memory (RAM) 13, communicatively connected to the at least one processor 11. The memory stores computer programs executable by the at least one processor. The processor 11 can perform various appropriate actions and processes based on the computer program stored in the ROM 12 or loaded from storage unit 18 into the RAM 13. The RAM 13 can also store various programs and data required for the operation of the electronic device 10. The processor 11, ROM 12, and RAM 13 are interconnected via a bus 14. An input / output (I / O) interface 15 is also connected to the bus 14.

[0080] Multiple components in electronic device 10 are connected to I / O interface 15, including: input unit 16, such as keyboard, mouse, etc.; output unit 17, such as various types of displays, speakers, etc.; storage unit 18, such as disk, optical disk, etc.; and communication unit 19, such as network card, modem, wireless transceiver, etc. Communication unit 19 allows electronic device 10 to exchange information / data with other devices through computer networks such as the Internet and / or various telecommunications networks.

[0081] Processor 11 can be a variety of general-purpose and / or special-purpose processing components with processing and computing capabilities. Some examples of processor 11 include, but are not limited to, a central processing unit (CPU), a graphics processing unit (GPU), various special-purpose artificial intelligence (AI) computing chips, various processors running machine learning model algorithms, digital signal processors (DSPs), and any suitable processor, controller, microcontroller, etc. Processor 11 performs the various methods and processes described above, such as the MBSE-based design method for a lunar space communication and navigation constellation system.

[0082] In some embodiments, the MBSE-based design method for a lunar-Earth space communication and navigation constellation system can be implemented as a computer program tangibly contained in a computer-readable storage medium, such as storage unit 18. In some embodiments, part or all of the computer program can be loaded and / or installed on electronic device 10 via ROM 12 and / or communication unit 19. When the computer program is loaded into RAM 13 and executed by processor 11, one or more steps of the MBSE-based design method for a lunar-Earth space communication and navigation constellation system described above can be performed. Alternatively, in other embodiments, processor 11 can be configured to perform the MBSE-based design method for a lunar-Earth space communication and navigation constellation system by any other suitable means (e.g., by means of firmware).

[0083] Various implementations of the systems and techniques described above herein can be implemented in digital electronic circuit systems, integrated circuit systems, field-programmable gate arrays (FPGAs), application-specific integrated circuits (ASICs), application-specific standard products (ASSPs), systems-on-a-chip (SoCs), complex programmable logic devices (CPLDs), computer hardware, firmware, software, and / or combinations thereof. These various implementations may include: implementations in one or more computer programs that can be executed and / or interpreted on a programmable system including at least one programmable processor, which may be a dedicated or general-purpose programmable processor, capable of receiving data and instructions from a storage system, at least one input device, and at least one output device, and transmitting data and instructions to the storage system, the at least one input device, and the at least one output device.

[0084] Computer programs used to implement the methods of the present invention may be written in any combination of one or more programming languages. These computer programs may be provided to a processor of a general-purpose computer, a special-purpose computer, or other programmable data processing device, such that when executed by the processor, the computer programs cause the functions / operations specified in the flowcharts and / or block diagrams to be performed. The computer programs may be executed entirely on a machine, partially on a machine, or as a standalone software package, partially on a machine and partially on a remote machine, or entirely on a remote machine or server.

[0085] In the context of this invention, a computer-readable storage medium can be a tangible medium that may contain or store a computer program for use by or in conjunction with an instruction execution system, apparatus, or device. A computer-readable storage medium may include, but is not limited to, electronic, magnetic, optical, electromagnetic, infrared, or semiconductor systems, apparatus, or devices, or any suitable combination thereof. Alternatively, a computer-readable storage medium may be a machine-readable signal medium. More specific examples of machine-readable storage media include electrical connections based on one or more wires, portable computer disks, hard disks, random access memory (RAM), read-only memory (ROM), erasable programmable read-only memory (EPROM or flash memory), optical fibers, portable compact disk read-only memory (CD-ROM), optical storage devices, magnetic storage devices, or any suitable combination thereof.

[0086] To provide interaction with a user, the systems and techniques described herein can be implemented on an electronic device having: a display device (e.g., a CRT (cathode ray tube) or LCD (liquid crystal display) monitor) for displaying information to the user; and a keyboard and pointing device (e.g., a mouse or trackball) through which the user provides input to the electronic device. Other types of devices can also be used to provide interaction with the user; for example, feedback provided to the user can be any form of sensory feedback (e.g., visual feedback, auditory feedback, or tactile feedback); and input from the user can be received in any form (including sound input, voice input, or tactile input).

[0087] The systems and technologies described herein can be implemented in computing systems that include backend components (e.g., as data servers), or middleware components (e.g., application servers), or frontend components (e.g., user computers with graphical user interfaces or web browsers through which users can interact with implementations of the systems and technologies described herein), or any combination of such backend, middleware, or frontend components. The components of the system can be interconnected via digital data communication of any form or medium (e.g., communication networks). Examples of communication networks include local area networks (LANs), wide area networks (WANs), blockchain networks, and the Internet.

[0088] A computing system can include clients and servers. Clients and servers are generally located far apart and typically interact through communication networks. The client-server relationship is created by computer programs running on the respective computers and having a client-server relationship with each other. The server can be a cloud server, also known as a cloud computing server or cloud host, which is a hosting product within the cloud computing service system to address the shortcomings of traditional physical hosts and VPS services, such as high management difficulty and weak business scalability.

[0089] This invention also provides a computer program product, including a computer program that, when executed by a processor, can implement the MBSE-based design method for a lunar space communication and navigation constellation system as provided in any embodiment of this application.

[0090] In the implementation of the computer program product, computer program code for performing the operations of this application can be written in one or more programming languages ​​or a combination thereof. Programming languages ​​include object-oriented programming languages ​​such as Java, Smalltalk, and C++, as well as conventional procedural programming languages ​​such as C or similar languages. The program code can be executed entirely on the user's computer, partially on the user's computer, as a standalone software package, partially on the user's computer and partially on a remote computer, or entirely on a remote computer or server. In cases involving remote computers, the remote computer can be connected to the user's computer via any type of network—including a local area network (LAN) or a wide area network (WAN)—or can be connected to an external computer (e.g., via the Internet using an Internet service provider).

[0091] It should be understood that the various forms of processes shown above can be used, with steps reordered, added, or deleted. For example, the steps described in this invention can be executed in parallel, sequentially, or in different orders, as long as the desired result of the technical solution of this invention can be achieved, and this is not limited herein.

[0092] The specific embodiments described above do not constitute a limitation on the scope of protection of this invention. Those skilled in the art should understand that various modifications, combinations, sub-combinations, and substitutions can be made according to design requirements and other factors. Any modifications, equivalent substitutions, and improvements made within the spirit and principles of this invention should be included within the scope of protection of this invention.

Claims

1. A method for designing a MBSE-based lunar-space communication navigation constellation system, characterized in that, include: A system-level architecture model of the Earth-Moon space communication and navigation constellation is constructed to obtain the Earth-Moon communication and navigation constellation system. The requirements of the Earth-Moon communication and navigation constellation system are modeled using SysML requirement diagrams to obtain the performance index requirements of different users in different functional aspects. Based on the orbit type in the Earth-Moon space communication and navigation constellation, a parameterized orbital mechanics model and a link transmission model are established. The target performance simulation model of the Earth-Moon communication and navigation constellation system is constructed based on the performance index requirements, the orbital mechanics model, and the link transmission model.

2. The method of claim 1, wherein, The system-level architecture model for constructing the Earth-Moon space communication and navigation constellation yields the Earth-Moon communication and navigation constellation system, including: Acquire at least one of the following segments in the Earth-Moon space communication and navigation constellation: the ground segment, the space segment, the lunar segment, and the user segment; The Earth-Moon communication and navigation constellation system is obtained by constructing each module contained in at least one of the ground segment, space segment, lunar segment, and user segment using the SysML module, and by defining the graph and system boundaries of the Earth-Moon space communication and navigation constellation using the SysML module.

3. The method according to claim 1, characterized in that, The requirements of the Earth-Moon communication and navigation constellation system are modeled using SysML requirement diagrams to obtain performance indicator requirements for different users in different functional aspects, including: To obtain the communication, navigation and timing function requirements of different users in the Earth-Moon communication and navigation constellation system; The SysML requirement diagram is used to model the requirements of different users in terms of communication, navigation and timing functions, and the performance index requirements of different users in different functions are obtained.

4. The method according to claim 1, characterized in that, The construction of the target performance simulation model for the Earth-Moon communication and navigation constellation system based on the performance index requirements and the orbital mechanics model and link transmission model includes: At least some of the SysML parameters in the SysML parameter diagram associated with the orbital mechanics model and the link transmission model are used as input parameters and input into the initial performance simulation model corresponding to the Earth-Moon communication and navigation constellation system to obtain the corresponding output parameters. If the output parameters meet the performance index requirements, the performance simulation model corresponding to the output parameters meeting the performance index requirements shall be used as the target performance simulation model. If the output parameters do not meet the performance requirements, the input parameters are dynamically adjusted, and the adjusted input parameters are input into the latest performance simulation model corresponding to the Earth-Moon communication and navigation constellation system until the corresponding performance requirements are met, thus obtaining the target performance simulation model.

5. The method according to claim 4, characterized in that, The performance simulation model includes at least one of the following: Inter-satellite link data simulation model; constellation autonomous orbit determination model; user link simulation model; user performance simulation model.

6. The method according to claim 5, characterized in that, The process of using at least a portion of the SysML parameters from the SysML parameter diagram associated with the orbital mechanics model and the link transmission model as input parameters, and inputting them into the initial performance simulation model corresponding to the Earth-Moon communication and navigation constellation system, yields corresponding output parameters, including at least one of the following: At least one of the translational point orbit parameters, Earth orbit parameters, lunar orbit parameters, satellite transmitting antenna parameters, satellite receiving antenna parameters, and link establishment parameters in the SysML parameter diagram associated with the orbital mechanics model and the link transmission model is used as input parameters and input to the inter-satellite link data simulation model corresponding to the Earth-Moon communication and navigation constellation system to obtain at least one of the inter-satellite link data, received power, and inter-satellite link delay between each satellite in the Earth-Moon communication and navigation constellation. At least one of the translational point orbit parameters, Earth orbit parameters, lunar orbit parameters, and inter-satellite link data in the SysML parameter diagram associated with the orbital mechanics model and the link transmission model is used as an input parameter and input into the constellation autonomous orbit determination model corresponding to the Earth-Moon communication and navigation constellation system to obtain the constellation autonomous orbit determination accuracy. At least one of the following parameters from the SysML parameter diagram associated with the orbital mechanics model and the link transmission model—the translational point orbit parameter, the Earth orbit parameter, the lunar orbit parameter, the user parameter, the satellite transmitting antenna parameter, the satellite receiving antenna parameter, and the satellite-user link establishment parameter—is used as input parameters and input into the user link simulation model corresponding to the Earth-Moon communication and navigation constellation system. This yields at least one of the following parameters: link data between each communication and navigation satellite and the user in the Earth-Moon communication and navigation constellation, user receiving power, and user link delay. At least some parameters from the SysML parameter diagram associated with the orbital mechanics model and the link transmission model are input into the user performance simulation model to obtain the communication and navigation performance of the Earth-Moon communication and navigation constellation for the user.

7. The method according to claim 6, characterized in that, The translation point orbit parameters include: translation point number, orbit type, number of satellites, plane amplitude, vertical amplitude, and phase; The Earth orbit parameters include: the total number of satellites in Earth orbit, the number of Earth orbital planes, relative phase parameters, orbital altitude, inclination, and eccentricity; The lunar orbital parameters include: the total number of lunar orbital satellites, the number of lunar orbital planes, relative phase parameters, orbital altitude, inclination, and eccentricity; The satellite transmitting antenna parameters include: transmitting power, transmitter antenna gain, and wavelength; The satellite receiving antenna parameters include: receiver antenna gain; The link establishment parameters include: link establishment frequency and beam angle; The user parameters include: user satellite orbital parameters or position and velocity.

8. An electronic device, characterized in that, The electronic device includes: At least one processor; and A memory communicatively connected to the at least one processor; wherein, The memory stores a computer program that can be executed by the at least one processor, the computer program being executed by the at least one processor to enable the at least one processor to execute the design method of the Earth-Moon space communication and navigation constellation system based on MBSE as described in any one of claims 1-7.

9. A computer-readable storage medium, characterized in that, The computer-readable storage medium stores computer instructions that cause a processor to execute the design method of the Earth-Moon space communication and navigation constellation system based on MBSE as described in any one of claims 1-7.

10. A computer program product, characterized in that, The computer program product includes a computer program that, when executed by a processor, implements the design method for a lunar-Earth space communication and navigation constellation system based on MBSE according to any one of claims 1-7.

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