Simulation Method, Device and System for Time-division Multiplexing Telemetry Frame Packing of Routing Spacecraft Channels

Abstract

A simulation method, device and system for time-division multiplexing telemetry framing of a routing spacecraft channel. The method includes: receiving simulation data, if the simulation data is telemetry data of a target spacecraft, calling a data source simulation model to perform real-time transmission virtual channel data source simulation processing on the telemetry data, so as to encapsulate the simulation data into real-time transmission target spacecraft virtual channel data units, and using an on-board fixed storage simulation model to store the data to be stored; if the data is simulation operation control command data, calling a downlink channel time-division multiplexing simulation model to perform telemetry framing simulation processing, so as to call a data source simulation model to perform real-time transmission virtual channel data source simulation processing according to the status bus information; publishing the telemetry frames sent by the downlink channel time-division multiplexing simulation model, advancing the simulation time, and obtaining the telemetry framing simulation result. The present invention realizes accurate simulation of the downlink channel framing process of a routing spacecraft, ensures that the spacecraft efficiently and accurately executes deep space exploration tasks, and saves resource costs.

Description

Technical Field

[0001] The present invention relates to the technical field of deep - space routing spacecraft, and particularly to a simulation method, device and system for time - division multiplexing telemetry framing of a routing spacecraft channel. Background Technique

[0002] In order to solve the problems of signal attenuation, severe arc - segment and bandwidth limitations in point - to - point communication between celestial bodies during deep - space exploration missions, it is a relatively mainstream approach at home and abroad to establish a deep - space relay communication link by deploying relay satellites, orbiting spacecraft, etc. Realizing data relay with the help of routing spacecraft can effectively improve the bandwidth and quality of data transmission of deep - space detectors, and can alleviate the impact on tracking continuity caused by communication arc - segment interruption through caching and playback mechanisms. Therefore, in addition to performing its own detection functions, the data relay, storage and scheduled downlink for multiple target spacecraft are one of the most important tasks of routing spacecraft.

[0003] In simulation modeling for testing and experimental verification, if the telemetry framing simulation requirements of routing spacecraft under the CCSDS - AOS system cannot be met, it will make the subsequent processes of spacecraft performing deep - space exploration missions, telemetry data acquisition and processing unable to be accurately implemented, resulting in significant losses in resources and economy, as well as problems such as low efficiency, poor accuracy in spacecraft mission execution, and waste of manpower and material resources. Summary of the Invention

[0004] Aiming at the problems existing in the prior art, the main purpose of the embodiments of the present invention is to provide a simulation method, device and system for time - division multiplexing telemetry framing of a routing spacecraft channel, to achieve precise simulation of the telemetry data framing process of the routing spacecraft, and to ensure that the spacecraft efficiently and accurately performs deep - space exploration missions.

[0005] To achieve the above object, an embodiment of the present invention provides a simulation method for time - division multiplexing telemetry framing of a routing spacecraft channel, and the method includes:

[0006] Receiving simulation data, if the simulation data is the telemetry data of the target spacecraft, then calling the pre - established data source simulation model to perform real - time relay virtual channel data source simulation processing on the simulation data, so as to encapsulate the simulation data into real - time relay target spacecraft virtual channel data units, and using the pre - established on - board fixed - storage simulation model to perform verification, classification and storage of the data to be stored according to the status bus information;

[0007] If the simulation data is simulation operation control command data, then calling the pre - established downlink channel time - division multiplexing simulation model to perform telemetry framing simulation processing on the simulation data, so as to call the data source simulation model to perform real - time relay virtual channel data source simulation processing according to the status bus information;

[0008] Obtain and publish the telemetry frames sent by the downlink channel time-division multiplexing simulation model, and advance the simulation time to obtain the telemetry framing simulation results; wherein, the telemetry framing simulation results are used to determine the relay link resource allocation of the on-orbit spacecraft during the execution of the detection task.

[0009] Optionally, in an embodiment of the present invention, the method further includes:

[0010] Perform parameter initialization processing according to preset configuration information, and perform instantiation processing on the downlink channel time-division multiplexing simulation model, the data source simulation model, and the on-board fixed storage simulation model;

[0011] Receive the simulation time information of each model sent by the downlink channel time-division multiplexing simulation model, the data source simulation model, and the on-board fixed storage simulation model, and use the simulation time information of each model to determine the simulation time.

[0012] Optionally, in an embodiment of the present invention, the method further includes: If the simulation data is simulation operation control command data, preset to execute the simulation operation control command, the flight program, and the delay instruction, and update the telemetry parameter values.

[0013] An embodiment of the present invention also provides a routing spacecraft channel time-division multiplexing telemetry framing simulation device, the device includes:

[0014] A data source simulation module, configured to receive simulation data. If the simulation data is the telemetry data of the target spacecraft, call the pre-established data source simulation model to perform real-time transmission virtual channel data source simulation processing on the simulation data, so as to encapsulate the simulation data into real-time transmission target spacecraft virtual channel data units, and use the pre-established on-board fixed storage simulation model to perform verification, classification, and storage of the data to be stored according to the status bus information;

[0015] A downlink channel simulation module, configured to, if the simulation data is simulation operation control command data, call the pre-established downlink channel time-division multiplexing simulation model to perform telemetry framing simulation processing on the simulation data, so as to call the data source simulation model for real-time transmission virtual channel data source simulation processing according to the status bus information;

[0016] A telemetry frame module, configured to obtain and publish the telemetry frames sent by the downlink channel time-division multiplexing simulation model, and advance the simulation time to obtain the telemetry framing simulation results; wherein, the telemetry framing simulation results are used to determine the relay link resource allocation of the on-orbit spacecraft during the execution of the detection task.

[0017] Optionally, in an embodiment of the present invention, the device further includes:

[0018] An initialization module, configured to perform parameter initialization processing according to preset configuration information, and perform instantiation processing on a downlink channel time-division multiplexing simulation model, a data source simulation model, and an on-board fixed storage simulation model;

[0019] A simulation time module, configured to receive the simulation time information of each model sent by the downlink channel time-division multiplexing simulation model, the data source simulation model, and the on-board fixed storage simulation model, and determine the simulation time by using the simulation time information of each model.

[0020] Optionally, in an embodiment of the present invention, the device further includes: a parameter update module, configured to, if the simulation data is simulation operation control command data, preset the execution of simulation operation control commands, flight programs, and delay instructions, and update the telemetry parameter values.

[0021] An embodiment of the present invention further provides a routing spacecraft channel time-division multiplexing telemetry framing simulation system, including: a telemetry simulation controller, a downlink channel time-division multiplexing simulation model, a data source simulation model, an on-board fixed storage simulation model, and a telemetry simulation status bus;

[0022] The telemetry simulation controller is configured to receive simulation data. If the simulation data is target spacecraft telemetry data, it calls the pre-established data source simulation model to perform real-time transmission virtual channel data source simulation processing on the simulation data; if the simulation data is simulation operation control command data, it calls the pre-established downlink channel time-division multiplexing simulation model to perform telemetry framing simulation processing on the simulation data; obtain and publish the telemetry frames sent by the downlink channel time-division multiplexing simulation model, and perform simulation time advancement to obtain a telemetry framing simulation result; wherein, the telemetry framing simulation result is used to determine the relay link resource allocation of the on-orbit spacecraft during the execution of the detection task;

[0023] The downlink channel time-division multiplexing simulation model is configured to perform downlink channel scheduling according to the current device simulation time and status bus information. If the current channel scheduling result is the routing spacecraft's own service data channel, it performs its own service telemetry virtual channel scheduling according to the status bus information of the telemetry simulation status bus, and transmits the scheduling result to the data source simulation model; according to the preset framing code rate, it encapsulates the real-time transmission target spacecraft virtual channel data unit generated by the data source simulation model into a telemetry frame, and performs verification and encoding on the telemetry frame;

[0024] The data source simulation model is configured to use the scheduling result to judge the virtual channel type, and according to the virtual channel type, perform real-time transmission virtual channel data source simulation, encapsulate the simulation data into a real-time transmission target spacecraft virtual channel data unit, and call the on-board fixed storage simulation model;

[0025] The on-board solid-state simulation model is used to query the simulation solid-state record data according to the data playback range in the telemetry simulation status bus and generate a delayed telemetry reading result for the data source simulation model to generate a delayed telemetry playback virtual channel data unit; according to the status bus information of the telemetry simulation status bus, verify, classify, and store the real-time transmission target spacecraft virtual channel data unit and the delayed telemetry playback virtual channel data unit.

[0026] Optionally, in an embodiment of the present invention, the telemetry simulation controller is further configured to perform parameter initialization processing according to preset configuration information, and perform instantiation processing on the downlink channel time-division multiplexing simulation model, the data source simulation model, and the on-board solid-state simulation model; receive the model simulation time information sent by the downlink channel time-division multiplexing simulation model, the data source simulation model, and the on-board solid-state simulation model, and use the model simulation time information to determine the simulation time.

[0027] Optionally, in an embodiment of the present invention, the downlink channel time-division multiplexing simulation model is further configured to use the simulation time, spacecraft telemetry framing, the most recent framing time, and the framing period to judge the downlink condition, and perform downlink channel scheduling simulation processing according to the downlink condition judgment result.

[0028] Optionally, in an embodiment of the present invention, the on-board solid-state simulation model includes a data playback module, a data writing module, and a storage space module;

[0029] The data playback module is used to read the corresponding telemetry from the storage space according to the preset playback rule; the data writing module is used to write various virtual channel data units generated by the data source simulation model into the storage space module according to time, source, and category.

[0030] The present invention also provides an electronic device, including a memory, a processor, and a computer program stored on the memory and executable on the processor. When the processor executes the program, the above method is implemented.

[0031] The present invention also provides a computer-readable storage medium, which stores a computer program executed by a computer to implement the above method.

[0032] The present invention also provides a computer program product, including a computer program / instructions. When the computer program / instructions are executed by a processor, the steps of the above method are implemented.

[0033] The present invention establishes a spacecraft telemetry simulation architecture including a simulation controller, a simulation status bus, a downlink channel time-division multiplexing simulation model, a data source simulation model, and an on-board fixed memory simulation model, simulates the framing process of routing spacecraft telemetry data packets, realizes accurate simulation of the downlink channel framing process of routing spacecraft under deep-space large-delay conditions, and is capable of providing a simulation environment alone or in cooperation with other models for pre-mission scenario demonstration and flight control software testing of deep-space exploration missions, ensuring that the spacecraft efficiently and accurately executes deep-space exploration missions and saving resource costs. BRIEF DESCRIPTION OF THE DRAWINGS

[0034] In order to more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the following will briefly introduce the drawings required for the description of the embodiments. Obviously, the drawings in the following description are only some embodiments of the present invention. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts.

[0035] Figure 1 It is a flowchart of a method for simulating the time-division multiplexing telemetry framing of a routing spacecraft channel according to an embodiment of the present invention;

[0036] Figure 2 It is a flowchart of determining the simulation time in an embodiment of the present invention;

[0037] Figure 3 It is a schematic structural diagram of a system for simulating the time-division multiplexing telemetry framing of a routing spacecraft channel according to an embodiment of the present invention;

[0038] Figure 4 It is a schematic diagram of the working process of deep-space routing spacecraft telemetry simulation framing according to an embodiment of the present invention;

[0039] Figure 5 It is a schematic diagram of the working process of on-board fixed memory simulation of a routing spacecraft according to an embodiment of the present invention;

[0040] Figure 6 It is a schematic structural diagram of a device for simulating the time-division multiplexing telemetry framing of a routing spacecraft channel according to an embodiment of the present invention;

[0041] Figure 7 It is a schematic structural diagram of a device for simulating the time-division multiplexing telemetry framing of a routing spacecraft channel according to another embodiment of the present invention;

[0042] Figure 8 It is a schematic structural diagram of a device for simulating the time-division multiplexing telemetry framing of a routing spacecraft channel according to yet another embodiment of the present invention;

[0043] Figure 9 It is a schematic structural diagram of an electronic device provided by an embodiment of the present invention. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0044] An embodiment of the present invention provides a routing spacecraft channel time-division multiplexing telemetry framing simulation method, device and system.

[0045] The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, rather than all the embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

[0046] As Figure 1 shown is a flowchart of a routing spacecraft channel time-division multiplexing telemetry framing simulation method according to an embodiment of the present invention. The execution subject of the routing spacecraft channel time-division multiplexing telemetry framing simulation method provided by the embodiment of the present invention includes but is not limited to a routing spacecraft telemetry simulation controller. The present invention establishes a spacecraft telemetry simulation architecture including a simulation controller, a simulation status bus, a downlink channel time-division multiplexing simulation model, a data source simulation model and an on-board fixed memory simulation model, simulates the process of framing routing spacecraft telemetry data, and realizes an accurate simulation of the downlink channel framing process of routing spacecraft under deep space large delay conditions. It can provide a simulation environment alone or in cooperation with other models for the scheme demonstration before the implementation of deep space exploration tasks and the testing of flight control software, ensure that the spacecraft efficiently and accurately executes deep space exploration tasks, and save resource costs. The method shown in the figure includes:

[0047] Step S1, receive simulation data. If the simulation data is target spacecraft telemetry data, call the pre-established data source simulation model to perform real-time transmission virtual channel data source simulation processing on the simulation data, so as to encapsulate the simulation data into real-time transmission target spacecraft virtual channel data units, and use the pre-established on-board fixed memory simulation model to perform verification, classification and storage of the data to be stored according to the status bus information;

[0048] Step S2, if the simulation data is simulation operation control command data, call the pre-established downlink channel time-division multiplexing simulation model to perform telemetry framing simulation processing on the simulation data, so as to call the data source simulation model for real-time transmission virtual channel data source simulation processing according to the status bus information;

[0049] Step S3, obtain and publish the telemetry frames sent by the downlink channel time-division multiplexing simulation model, and perform simulation time advancement to obtain the telemetry framing simulation result; wherein, the telemetry framing simulation result is used to determine the relay link resource allocation of the on-orbit spacecraft during the execution of the exploration task.

[0050] Among them, the present invention utilizes the constructed routing spacecraft channel time-division multiplexing telemetry framing simulation system to execute the above simulation method, so as to simulate the telemetry data acquisition, framing and storage processes of the routing spacecraft in the deep space relay communication link, and is capable of providing a simulation environment alone or in cooperation with other models for the scheme demonstration before the implementation of the deep space exploration mission and the flight control software test. The specific simulation process is described as follows.

[0051] As an embodiment of the present invention, as Figure 2 shown, the method further includes:

[0052] Step S4, perform parameter initialization processing according to the preset configuration information, and instantiate the downlink channel time-division multiplexing simulation model, data source simulation model and on-board fixed storage simulation model;

[0053] Step S5, receive the simulation time information of each model sent by the downlink channel time-division multiplexing simulation model, data source simulation model and on-board fixed storage simulation model, and determine the simulation time by using the simulation time information of each model.

[0054] Among them, the telemetry simulation controller completes the initialization operation of the system according to the preset configuration information, instantiates the pre-established downlink channel time-division multiplexing simulation model, data source simulation model, on-board fixed storage simulation model and telemetry simulation state bus, and completes the initial state settings such as the simulation step length.

[0055] Furthermore, the telemetry simulation controller receives the simulation time information sent by other simulation models, thereby maintaining and determining the simulation time of the system, and broadcasting it to each model in the system.

[0056] In this embodiment, the telemetry simulation controller receives data from an external simulation device. If it is simulation operation control command data, it executes the response, changes the relevant information of the state bus or terminates the system operation; if it is the telemetry data of the target spacecraft, it calls the pre-established data source simulation model to perform real-time transmission virtual channel data source simulation processing on the simulation data; otherwise, if it is simulation operation control command data, it executes the telemetry framing simulation processing.

[0057] Among them, the method further includes: if the simulation data is simulation operation control command data, preset the execution of simulation operation control commands, flight programs and delay instructions, and update the telemetry parameter values.

[0058] In this embodiment, the real-time relay virtual channel data source simulation processing specifically includes: If the current system receives telemetry data of the target spacecraft, the real-time relay target spacecraft virtual channel data unit CADU is encapsulated and generated according to the format regulations; otherwise, a filled CADU is generated. The on-board fixed memory simulation model performs simulation storage of the real-time relay target spacecraft virtual channel data unit CADU data, completes the verification and classification of the data to be stored according to the status bus information of the telemetry simulation status bus, and updates the fixed memory storage status and data information after writing to the simulation fixed memory. The downlink channel time-division multiplexing simulation model encapsulates various types of CADU data generated by the data source simulation model that meet the current simulation time into a complete AOS telemetry frame, that is, a telemetry frame, according to the frame code rate requirements of the task format, and performs corresponding verification and encoding work. The telemetry simulation controller receives the telemetry frame, publishes it outside the system, and advances the simulation time, thereby completing the simulation process and obtaining the corresponding telemetry frame simulation result.

[0059] Furthermore, the telemetry frame simulation processing specifically includes: The downlink channel time-division multiplexing simulation model performs downlink channel scheduling according to the current system simulation time and status bus information. Determine whether the current channel scheduling result is the routing spacecraft's own service data channel. If so, perform its own service telemetry virtual channel scheduling according to the information in the status bus, and transfer the scheduling result to the data source simulation model to determine the virtual channel type occupied by time division in the current telemetry frame; otherwise, directly determine the virtual channel type occupied by time division in the current telemetry frame. Specifically, determine the virtual channel type occupied by time division in the current telemetry frame. If it is its own service data telemetry virtual channel, perform service data telemetry source packet scheduling according to the telemetry frame conditions and constraints, and sequentially generate the routing spacecraft source packet data unit EPDU, MPDU, and VCDU; if it is a real-time relay virtual channel, perform real-time relay virtual channel data source simulation. If it is an on-board storage delay telemetry playback virtual channel, the on-board fixed memory simulation model queries the simulation fixed memory record data and generates a delay telemetry read result according to the data playback range and requirements in the status bus, for the data source simulation model to generate the delay telemetry playback virtual channel data unit CADU. The on-board fixed memory simulation model performs simulation storage of the real-time relay target spacecraft virtual channel data unit CADU data, completes the verification and classification of the data to be stored according to the status bus information of the telemetry simulation status bus, and updates the fixed memory storage status and data information after writing to the simulation fixed memory. The downlink channel time-division multiplexing simulation model encapsulates various types of CADU data generated by the data source simulation model that meet the current simulation time into a complete AOS telemetry frame, that is, a telemetry frame, according to the frame code rate requirements of the task format, and performs corresponding verification and encoding work. The telemetry simulation controller receives the telemetry frame, publishes it outside the system, and advances the simulation time, thereby completing the simulation process and obtaining the corresponding telemetry frame simulation result.

[0060] Specifically, the telemetry framing simulation results finally obtained by the present invention include various types of CCSDS-AOS telemetry frames such as the service telemetry of the routing spacecraft itself in the deep space relay link, the playback of its own delay telemetry frames, the real-time transmission of the target spacecraft telemetry frames, and the playback of the target spacecraft delay telemetry frames. The present invention can be applied to the flight control scheme design and demonstration in the early stage of deep space exploration missions, the testing of ground application software systems, the multi-position collaborative drills among mission participating units, and provide simulation test support for the verification of the on-orbit relay link resource planning and allocation strategies during the execution of exploration missions, thereby solving problems such as signal attenuation and severe limitations of arcs and bandwidth in point-to-point communication in deep space exploration missions.

[0061] Specifically, the simulation process in the present invention is specifically applied to the flight control drills of Mars exploration missions and the on-orbit synchronous verification of the relay communication strategies of Mars orbiters, and good results have been achieved. In the preparation of the fourth phase of a certain project, in view of the actual mission requirements of a certain relay satellite as a routing spacecraft to support the relay communication of multiple lunar probes, a simulation environment for demonstration experiments is provided, thereby ensuring the efficiency and accuracy of spacecraft mission execution.

[0062] In a specific embodiment of the present invention, as Figure 3 shown is a schematic structural diagram of a telemetry framing simulation system for time-division multiplexing of a routing spacecraft channel according to an embodiment of the present invention. The system shown in the figure includes: a telemetry simulation controller, a downlink channel time-division multiplexing simulation model, a data source simulation model, an on-board fixed memory simulation model, and a telemetry simulation status bus.

[0063] The telemetry simulation controller is used to receive simulation data. If the simulation data is the telemetry data of the target spacecraft, it calls the pre-established data source simulation model to perform real-time transmission virtual channel data source simulation processing on the simulation data; if the simulation data is the simulation operation control command data, it calls the pre-established downlink channel time-division multiplexing simulation model to perform telemetry framing simulation processing on the simulation data; obtains and publishes the telemetry frames sent by the downlink channel time-division multiplexing simulation model, and advances the simulation time to obtain the telemetry framing simulation results; among them, the telemetry framing simulation results are used to determine the relay link resource allocation of the on-orbit spacecraft during the execution of the exploration mission.

[0064] The downlink channel time-division multiplexing simulation model is used to perform downlink channel scheduling according to the current system simulation time and status bus information. If the current channel scheduling result is the service data channel of the routing spacecraft itself, it performs its own service telemetry virtual channel scheduling according to the status bus information of the telemetry simulation status bus, and transfers the scheduling result to the data source simulation model; according to the preset framing code rate, it encapsulates the real-time transmission target spacecraft virtual channel data unit generated by the data source simulation model into a telemetry frame, and performs verification and coding on the telemetry frame;

[0065] The data source simulation model is used to determine the virtual channel type based on the scheduling result, and according to the virtual channel type, perform real-time transmission virtual channel data source simulation, encapsulate the simulation data into the real-time transmission target spacecraft virtual channel data unit, and call the on-board fixed storage simulation model;

[0066] The on-board fixed storage simulation model is used to query the simulation fixed storage record data and generate a delayed telemetry reading result according to the data playback range in the telemetry simulation status bus, for the data source simulation model to generate a delayed telemetry playback virtual channel data unit; according to the status bus information of the telemetry simulation status bus, perform verification, classification and storage on the real-time transmission target spacecraft virtual channel data unit and the delayed telemetry playback virtual channel data unit.

[0067] Among them, the target spacecraft refers to the spacecraft that performs the exploration activities around and on the surface of the celestial body and in the deep space environment during the deep space exploration mission, including various types such as orbiters, rovers, landers, and space probes. Due to the influence of distance and ground visibility, the data collected and generated by it needs to be transmitted to the ground with the help of a routing spacecraft. The routing spacecraft refers to the spacecraft that is mainly used for data relay, continuous tracking and orbit control and measurement and control services for the target spacecraft during the deep space exploration mission, and is used to make up for the deficiency of the tracking and measurement and control coverage of the ground measurement and control station. It is an important means for high-speed data transmission and multi-target measurement and control in deep space exploration.

[0068] Furthermore, the AOS telemetry system refers to a set of advanced on-orbit data system transmission and processing protocols adopted and released by the Consultative Committee for Space Data System (CCSDS) of the International Space Data System, serving air-to-air and air-to-ground data transmission and processing. The virtual channel (VC) is a concept introduced by the AOS protocol. The virtual channel divides a physical channel into several independent logical data channels, so that the high-level data streams with different service requirements can share a physical channel through independent virtual channels.

[0069] In this embodiment, as Figure 3 shown, in order to meet the telemetry simulation requirements of the routing spacecraft in various deep space exploration missions and improve the reusability of the system of the present invention, a deep space relay link routing spacecraft telemetry simulation architecture is designed. Through low-coupling module function division and abstract data and interface design, the system has high generality and flexibility. The simulation architecture is as Figure 3As shown in the figure, it includes five parts: the telemetry simulation controller of the routing spacecraft, the time-division multiplexing simulation model of the downlink channel, the virtual channel data unit simulation model, the on-board solid-state memory simulation model, and the telemetry simulation state bus of the routing spacecraft. It realizes the simulation of various CCSDS-AOS telemetry frames such as the on-board service telemetry of the routing spacecraft itself, the real-time transmission of the target spacecraft telemetry, the playback of its own delayed telemetry, and the playback of the delayed telemetry of the target spacecraft in the deep space relay link.

[0070] Among them, the telemetry simulation controller of the routing spacecraft: It is used to control the behavior of the system in the simulation loop calculation with the simulation step as the unit, including simulation time maintenance and publication (label 3), external data processing and event response (label 2), calling the downlink channel simulation model to execute the framing behavior within the simulation step unit time (label 7), completing data interaction with other external models or systems through the publish-subscribe mechanism (labels 1, 5), updating the telemetry simulation status information (label 4), etc. The configuration file reading and initialization settings of the system of the present invention are also completed by the controller.

[0071] Furthermore, the time-division multiplexing simulation model of the downlink channel selects the type and format of the downlink channel for system-simulated telemetry according to the telemetry simulation status information and the pre-installed configuration information, realizes the acquisition scheduling of the channel simulation data source (label 11) and the scheduling of the virtual channel of the on-board service telemetry of the routing spacecraft itself (labels 8, 10), receives and processes the CADU simulation result (label 9), and realizes the encapsulation of the channel access unit CADU to generate a complete AOS telemetry frame (label 6) for the telemetry simulation controller to publish.

[0072] Furthermore, the data source simulation model includes the on-board service telemetry simulation module of the routing spacecraft, the target spacecraft's transmitted telemetry processing module, and the memory delayed telemetry reading module. It simulates the corresponding virtual channel data domain according to the scheduling of the time-division multiplexing simulation model of the downlink channel, and its result is used for storage (label 13) and the framing of the complete telemetry frame (label 9).

[0073] Furthermore, the on-board solid-state memory is an important functional component of the routing spacecraft in the deep space relay link. Using the on-board solid-state memory to record and store its own telemetry and the target spacecraft's transmitted telemetry in the orbital arc section where the routing spacecraft and the ground station are not visible, and then playback and downlink in the visible arc section is an important means to ensure the integrity of the downlink data in the deep space relay link. The on-board solid-state memory simulation model is used to simulate the processes such as data storage, read-write control (labels 14, 15), and playback framing (label 12), so as to improve the authenticity of the routing spacecraft's downlink simulation data.

[0074] Further, the routing spacecraft telemetry simulation status bus is used to store the status information of the system simulation operation, has a unique instance within the system, and can be shared and accessed by the above-mentioned components. As an information bulletin board, the status bus can transmit the control information of the telemetry simulation (label 4), and report and summarize the working status of each model (label 16). Each status information has one and only one publisher, who is responsible for maintaining and updating it; the number of subscribers is unlimited, and they respond according to the information change, so as to realize the automatic flow of the telemetry simulation calculation process.

[0075] As an embodiment of the present invention, the telemetry simulation controller is further used to perform parameter initialization processing according to the preset configuration information, and perform instantiation processing on the downlink channel time-division multiplexing simulation model, the data source simulation model, and the on-board fixed storage simulation model; receive the simulation time information of each model sent by the downlink channel time-division multiplexing simulation model, the data source simulation model, and the on-board fixed storage simulation model, and use the simulation time information of each model to determine the simulation time.

[0076] In this embodiment, the specific content of the system executing the routing spacecraft telemetry framing control method based on the simulation status bus is described as follows.

[0077] In actual deep space exploration missions, the spacecraft downlink telemetry framing includes multiple relatively complex processing and control processes such as status setting, sensor data acquisition and storage, source packet scheduling control, virtual channel scheduling control, and channel coding. During the process, various types and granularities of data such as telemetry parameters, encapsulated protocol data units EPDU, multiplexed protocol data units MPDU, bit stream protocol data units BPDU, virtual channel data units VCDU, and framing are generated. In order to perform a "black box" simulation of this process, a telemetry framing control method based on the simulation status bus is implemented on the basis of the telemetry simulation architecture.

[0078] The status bus is used to record and reflect the key status information that affects the execution of each model in the system, and realize the transmission of status messages between modules. The status bus includes four status categories: simulation operation control message, downlink channel simulation status information, data source simulation status information, and fixed storage read / write control information.

[0079] Strict write control is implemented for the fields of various types of information, and the only allowed publisher for writing and modification is set according to the predetermined configuration information. Any modification of a field will broadcast a change message within the system to remind the subscribers of this field to obtain the latest status and make a response. The information and access rights included in the routing spacecraft telemetry simulation status bus are shown in Table 1 specifically.

[0080] Table 1 Composition of the routing spacecraft telemetry simulation status bus

[0081]

[0082]

[0083] The system of the present invention performs the following steps to execute the routing of spacecraft telemetry simulation framing: Figure 4 As shown in the figure, the simulation state bus serves as the medium for recording and transmitting process control messages during the telemetry simulation framing process. It interacts with all steps of the framing process, but other than reporting status field changes, it does not actively publish data to the outside world to affect process execution. Therefore, it is not shown in the figure for clarity.

[0084] The specific steps are as follows:

[0085] (1) The telemetry simulation control module completes the initialization operation of the system of the present invention according to the pre-set configuration information, instantiates the downlink channel time-division multiplexing simulation model, the data source simulation model, the on-device storage simulation model and the telemetry simulation state bus, and completes the simulation step length t step The initial state is set; at this time, the simulation time of the system is T sim (Simulation time) is equal to Beijing time (or computer host system time) T BJ , the time difference between simulation time and Beijing time Δt sim_BJ =T sim -T BJ =0;

[0086] (2) Execute the simulation propulsion cycle of the system of the present invention. Receive the simulation time information T sent by other simulation models input , based on which the simulation of the system is maintained and broadcast to each model in the system:

[0087] Calculate the time difference Δt between the acquisition time information and the simulation time of this system input_sim =T input -T sim .

[0088] ·like ( The error threshold allowed for time accuracy is considered), indicating that time advancement is approved or the system performs a time jump operation, and the system simulation time T is updated. sim =T input , and record the time difference Δt between the simulation time of this step and the host system time sim_sys =T sim -GetsSystemTime(). GetsSystemTime() is a system function that can obtain the host system time with an accuracy much larger than the step size;

[0089] ·like or Δt input_sim <0, indicating that the time advancement is not approved or the time has an error jump back, the system continues with the original T sim Run the simulation framing loop for the time base.

[0090] In summary, the simulation time of the system of the present invention increases in a uniform stepped manner with the step size as the unit;

[0091] (3) Receive data from an external simulation device. If it is simulation operation control command data, execute the response, change the relevant information of the status bus or terminate the system operation in step 0; if it is telemetry data of the target spacecraft, jump to step 0; otherwise, execute the simulation telemetry framing process;

[0092] (4) The simulation framing process performs downlink channel scheduling according to the current system simulation time and status bus information. Determine whether the current channel scheduling result is the routing spacecraft's own service data channel. If so, execute step 0; otherwise, execute step 0;

[0093] (5) According to the information in the status bus, perform the scheduling of the virtual channel of the own service telemetry, transfer the scheduling result to the data source simulation model, and execute step 0;

[0094] (6) Determine the type of virtual channel occupied by the time division in the current telemetry frame. If it is the virtual channel of the own service data telemetry, execute the scheduling of the service data telemetry source packet according to the telemetry framing conditions and constraints, and generate the routing spacecraft source packet data units EPDU, MPDU, and VCDU in sequence; if it is the real-time transmission virtual channel, execute step 0; if it is the virtual channel of the on-board storage delay telemetry playback, execute step 0;

[0095] (7) Perform the simulation of the data source of the real-time transmission virtual channel. If the current system receives telemetry data of the target spacecraft, encapsulate and generate the data CADU of the real-time transmission target spacecraft virtual channel according to the format regulations. Otherwise, generate the filled CADU, and execute step 0 data storage and step 0 complete telemetry frame generation;

[0096] (8) The on-board fixed storage simulation model queries the simulation fixed storage record data and generates the delay telemetry reading result according to the data playback range and requirements in the status bus, for the data source simulation model to generate the delay telemetry playback virtual channel data unit CADU, update the status bus and execute step 0 data storage and step 0 complete telemetry frame generation;

[0097] (9) Perform the simulation storage of the virtual channel data unit CADU data, complete the verification and classification of the data to be stored according to the status bus information, write it into the simulation fixed storage, and then update the fixed storage status and data information;

[0098] (10) According to the framing code rate requirements, encapsulate various CADU data generated by the data source simulation model that meet the current simulation time into a complete AOS telemetry frame according to the task format requirements, perform the corresponding verification and encoding work, and publish it outside the system;

[0099] (11) When the simulation framing process is completed, the system of the present invention sends a time advancement request to the time management device or members of the simulation system, applying to advance the simulation time in units of step size. If approved, step 0 is executed; if the time advancement is not approved, return to step 0 to execute the simulation framing again.

[0100] (12) If a simulation stop command is received, stop running and the process ends.

[0101] As an embodiment of the present invention, the downlink channel time-division multiplexing simulation model is also used to judge the downlink conditions by using the simulation time, spacecraft telemetry framing, the most recent framing time, and the framing period, and perform downlink channel scheduling simulation processing according to the judgment result of the downlink conditions.

[0102] In this embodiment, the specific content of the system executing the routing spacecraft downlink channel simulation scheduling method is described as follows.

[0103] Due to the limitation of the downlink channel bandwidth in deep space exploration, various types of telemetry data such as the on-board service telemetry of the routing spacecraft, the telemetry relayed by the target spacecraft, and the fixed storage playback delay telemetry need to occupy the downlink channel in the form of time-division multiplexing within the limited bandwidth and be transmitted back to the ground TT&C equipment. During the mission, by coordinating the framing period of the AOS telemetry frame and the priority of various data acquisitions, the orderly generation and downlink of telemetry data are controlled to ensure the timeliness and integrity of key information to the greatest extent on the basis of avoiding data accumulation.

[0104] In the routing spacecraft downlink telemetry simulation, the time-division multiplexing of various simulation data sources for the channel is realized through the downlink channel scheduling method, and the scheduling process on the simulator is carried out through a scheduling strategy based on dynamic control of simulation time and priority.

[0105] Specifically, record the telemetry framing period of a certain routing spacecraft as t fram , which contains n multiplexed data sources, and their priorities are Prd = p cadu [i], and the initial p cadu [i] ∈ N. The generation period of each data source is Trd = t cadu [i], and the latest downlink time is recorded as T cadu_recent_frame [i]

[0106] Suppose the simulation time of the jth simulation step of the system of the present invention is T sim , and the most recent framing time of the spacecraft telemetry simulation framing within this step is T frame , obviously T sim < T frame < T sim + t step .

[0107] Execute the telemetry framing simulation process several times within one simulation step length. It is controlled by the simulation logic propulsion module of the telemetry simulation controller of the routing spacecraft and executed as many times as possible without striding over the step length. The framing simulation process is as follows:

[0108] 1) If GetsSystemTime() + Δt sim_sys -T frame ≥t fram , it indicates that the framing time has arrived, and start telemetry framing;

[0109] 2) Update the most recent telemetry framing time T frame =GetsSystemTime() + Δt sim_sys . Based on priority scheduling, elect the data source that satisfies p cadu [k]=argmax(Prd) as the framing content;

[0110] 3) If there are m data sources with the same priority, then calculate Δt = T cadu_recent_frame [m] + t cadu [m] - T frame for each data source in turn. Δt≥0 means that the data source has not reached the downlink time yet, and Δt is the time to wait. Skip this data.

[0111] If Δt < 0, its modulus is the lag duration of the current data source's downlink. Select the data source k that satisfies argmin(Δt) as the election result, and add the correction parameter :

[0112] p′=p cadu [k]

[0113]

[0114] where , which is used to dynamically adjust the priority while avoiding affecting the overall distribution of the priority due to the correction behavior:

[0115]

[0116] 4) Execute the periodic judgment of the data source k. If T frame -T cadu_recent_frame [k]≥t cadu [k], it means that this data source meets the downlink period, and then preempt the channel bandwidth to start downlink. Update t cadu_recent_frame [k]=T frame ;

[0117] 5) If T frame -T cadu_recent_frame [k]<tcadu [k], it means that the data source does not meet the downlink conditions. Restore its priority to the initial state p cadu [m] = p′, seek the next priority data to satisfy p cadu [j] = argmax(Prd); j! = k, return to step 3);

[0118] 6) Data generation from each data source is unaffected by downlink scheduling. Data is generated within the data source simulation model according to its generation cycle and conditions, and is sent to the device's persistent simulation model for storage and playback as required. In addition to subtle adjustments during the aforementioned process, data source downlink priority can also undergo significant changes based on data generation conditions (e.g., repeated generation failures) and system operating mode changes (e.g., responding to a remote control command to stop a certain type of data). If no data is available from any data source at the telemetry framing moment, filler data is used to occupy the channel.

[0119] 7) Perform telemetry encapsulation, verification and other operations to complete a framing process, and return to 1) to execute again.

[0120] In this way, the simulation of the telemetry framing process of the routing spacecraft is realized, which satisfies the independent generation of various types of data such as the routing spacecraft's own telemetry, the target spacecraft's transmitted telemetry, and the storage delay telemetry, as well as the time-sharing multiplexing of the downlink channel.

[0121] At the data source generation level, if the data source is telemetry transmitted from the target spacecraft, memory playback telemetry, or other sources, it is directly encapsulated into telemetry frames after receiving or reading. If the data is the routing spacecraft's own service data, it is also necessary to simulate the virtual channel scheduling and source packet scheduling of the AOS packetized telemetry mechanism to control the proportion of different virtual channel data and different telemetry source packets in the service telemetry. Virtual channel scheduling and source packet scheduling are generally implemented through proportional control and periodic judgment, and will not be detailed here.

[0122] As an embodiment of the present invention, the on-device persistent storage simulation model includes a data playback module, a data writing module and a storage space module.

[0123] Among them, the data playback module is used to read the corresponding telemetry from the storage space according to the preset playback rules; the data writing module is used to write various virtual channel data units generated by the data source simulation model into the storage space module according to time, source, and category.

[0124] In this embodiment, the specific content of the system executing the routing spacecraft on-board storage simulation method is described as follows.

[0125] In deep space relay communication links, one of the core functions of the routing spacecraft is to relay and bridge the data of the target spacecraft. In the arc segment where both the routing spacecraft and the target spacecraft are invisible to the ground, the main means to solve the insufficient real-time communication coverage rate between space and ground in deep space exploration missions is to store the telemetry data in the on-board solid state memory of the routing spacecraft and then replay and downlink it in the arc segment where the routing spacecraft is visible to the ground.

[0126] The on-board solid state memory simulation model of the routing spacecraft consists of three parts: a data playback module, a data writing module, and a solid state memory management and storage space module. Data playback is used to read the corresponding telemetry from the storage space according to the playback requirements; the data writing module is responsible for writing the virtual channel unit data of various simulated telemetries generated by the data source simulation model into the storage space according to time, source, category, etc.; the on-board solid state memory simulation model includes two sub-modules: data reading and writing control and simulation storage space: data reading and writing control is used to control the overall business flow of this model and schedule and promote the work of other modules in the model. The simulation storage space simulates the entity of the on-board storage space of the routing spacecraft and is used to record various telemetry data generated by the routing spacecraft itself and transmitted on behalf of the target spacecraft. According to the characteristics of specific mission data, the simulation storage space can be implemented in various ways such as database tables, text files, shared memory blocks, etc. in practical applications.

[0127] (1) On-board solid state memory simulation method

[0128] On actual routing spacecraft, on-board solid state memory usually uses memories such as SDRAM (Synchronous Dynamic Random Access Memory) and FLASH (Non-Volatile Flash Memory). Limited by the storage space, data may be recorded in binary blocks, compression algorithms, etc.

[0129] In simulation, since both recording and playback are performed in units of whole frames for reading and writing operations, from the perspective of implementation convenience and readability, the data content is recorded in the form of hexadecimal strings in pages or sub-database tables, without considering details such as memory structure, number of rows and columns, and refresh rate. The simulation memory is a logical concept composed of several data page (table) entities recording simulation data.

[0130] At the same time, in order to meet the simulation requirements for on-demand playback of stored data by time and address, it is necessary to establish an on-board solid state memory operation protocol for the routing spacecraft simulator to standardize the definition of the simulation memory, simulation data pages (tables), and simulation telemetry data frames and regulate the operation behavior. The data management module, data writing module, and data reading module implement access and operation on the simulation solid state memory according to this protocol.

[0131] The on-board solid state memory operation protocol for the simulator includes two parts: an interface protocol and a control protocol.

[0132] 1) Interface protocol: It is divided into a simulation memory description interface, a data paging (table) description interface, and a data frame description interface.

[0133] a. The simulation memory description interface is defined as I s = <M, F, S, J>.

[0134] Among them, M is the metadata of this interface, including the memory access ID, the size of the physical fixed storage space on the corrector and the access address mapping algorithm, the number of corresponding simulation data paging (tables), whether circular writing is allowed, etc.; F is the data admission information, defining the requirements for the telemetry data format that can be written into this memory, including the spacecraft identifier, length, etc.; S is the memory status information, recording whether the current simulation memory is readable and writable, the space occupancy, and the index of the current written data paging (table); J is the set of index information of all data paging (tables) contained in this memory, including the paging ID and the access address, etc.

[0135] b. The data paging (table) description interface is defined as I t = <m, f i , s i , f i >.

[0136] Among them, m is the metadata of this data paging (table), including the access ID, the size of the physical fixed storage space on the corrector and the start and end ranges of the access address, the memory ID it belongs to, etc.; f i is the data admission information of this paging (table), which is a subset of F in the I s interface, f i ∈I s .F; s i is the status information of this paging (table), including the writing status, the space occupancy, the simulation time range of the recorded data, etc.; j i is the index information of this paging (table), j i ∈I s .J.

[0137] c. The simulation data frame description interface is defined as I d = <T, P, A>.

[0138] Among them, T is the time information of the data frame, including the simulation time when the routing spacecraft generates / receives the telemetry data of this frame, the time on the telemetry frame device, and the simulation time when the telemetry frame is stored in the library; P is the data frame attribute information, including the spacecraft identifier, the data length, the virtual channel identifier, and the physical fixed storage address on the mapper; A is the content of the telemetry data frame.

[0139] 2) Control protocol: The control protocol is divided into two parts: positioning control and read / write control.

[0140] The positioning control is used to determine the data reading position and data writing position in the simulation fixed storage, and it defines L = <d tgt ,t,a,S info >. d target is the basic information of the data to be read or written, including spacecraft identification, data type, etc.; t and a are the time information and address information of the data respectively, and they cannot be empty at the same time; S info is the output, which is the result of data positioning, including the simulation memory id where the read / write data is located, the data paging index, the data pointer position, etc.

[0141] The read / write control is defined as C = <ot,S info ,DF,c,Or>. ot represents the operation type, which is divided into read, write, and delete; S info is the position information in the simulation fixed storage for performing the read / write operation; DF is the data frame content, which is an input parameter during the write operation and an output for the rest of the operations, and it can be empty; c is the data verification result, and Or is the read / write operation result identifier.

[0142] (2) On-board fixed storage simulation workflow

[0143] During the working process of the on-board fixed storage simulation model, each module executes its own simulation process, which are independent of each other and run in parallel asynchronously. The interaction of module states is realized by routing the fixed storage read / write control information in the spacecraft telemetry simulation state bus, and the transfer of telemetry data to be written or read out is realized by sharing a data linked list. As Figure 5 shown.

[0144] The on-board fixed storage simulation includes three sub-processes, which are respectively:

[0145] 1. Simulation fixed storage management sub-process

[0146] (1) The simulation fixed storage management sub-module initializes this model according to the "simulation fixed storage basic information" in the simulation state bus to determine information such as the type, number, and spatial size of the fixed storage, and the data types allowed to be stored;

[0147] (2) The simulation fixed storage management sub-module controls the simulation storage space sub-module to generate data record paging instances, defines the attributes and indexes of each data page, and sends read and write loop start signals to the data playback module and the data writing model;

[0148] (3) After initialization, the fixed storage management and storage space modules carry out their own simulation loops. First, according to the simulation time management logic, the T sim during model simulation is updated and broadcast, and wait to receive the data to be written sent by the data source simulation model;

[0149] (4) For all types of data to be written received, if the timestamp information T in the data satisfies source_data ≤T sim , then store it in the temporary cache in chronological order;

[0150] (5) Check whether there is any read data in the data read cache, and use all the data that satisfies the read timestamp T of the data delayed_data_read ≤T sim as the input of the memory delay telemetry reading module and transfer it to the data source simulation model. Feed back the read result to the telemetry simulation controller ( Figure 3 item number 17 in the figure) to modify the reading range of the "delay telemetry playback setting information" in the status bus.;

[0151] (6) Receive the simulation operation control command. If the end command is received, clear the simulation storage space and broadcast an end message inside the model to end the operation of this model. Otherwise, return to step 3) and execute the above process again. To improve efficiency, the persistent operation of writing data is completed by the simulation storage space sub-module at a certain period.

[0152] To avoid excessive read and write data at a certain moment resulting in too long a single cycle time consumption, the threshold of the maximum number of frames of data written and read per single time can be set in steps (4) and (5).

[0153] 2. Data writing sub-process

[0154] (1) The data writing module receives the control command of the simulation fixed storage management sub-module to create an instance, and starts the writing simulation loop after performing the initialization settings. The default data writing status flag WriteStatus is 0 (0 means normal writing, 1 means the data paging is full, and 2 means the available space of the fixed storage of this data type is full);

[0155] (2) Obtain the current simulation time T at the start of each loop sim , and check whether there is any data to be written. If not, repeat this step;

[0156] (3) If there is a writing requirement, take out the earliest frame stored in the writing cache, that is, the data frame that satisfies min(T source_data ) is recorded as String strDataWrite, and perform the identification and verification of information such as data type, format, and spacecraft identification.

[0157] (4) If the fixed memory write enable status in the simulation status bus is set to allow writing, the data writing module determines the current writing location based on the previous write status WriteStatus. It differentiates among three cases: normal writing to the current data paging, finding the next available paging for writing when the current paging is full, and overwriting and writing again when the fixed memory is full. Then, it writes strDataWrite to the target paging and updates the WriteStatus value according to the writing result.

[0158] (5) Update the "write pointer" and "data record information" to the simulation status bus. If the stop running command is not received, jump to 2) to execute the next loop; otherwise, end the operation of this module.

[0159] 3. Data playback sub - process

[0160] (1) After receiving the control command from the simulation fixed memory management sub - module and completing its own instantiation, the data playback module starts the read simulation loop. Set the model read status ReadStatus to 0 (0 means read completed, 1 means new read task, 2 means normal read, 3 means this data paging has been completely read, - 1 means read failed).

[0161] (2) At the start of each loop, obtain the latest simulation time T sim , check whether there is a data reading requirement in the "delay telemetry playback setting information" in the simulation status bus, and whether the fixed memory read enable status in the simulation status bus is set to allow reading. If not, repeat this step;

[0162] (3) If there is a reading requirement, the data playback module determines the current reading location based on the previous read status ReadStatus. It differentiates among three cases: re - finding the data paging index according to the playback range and reading based on the read pointer position, sequentially reading at the current paging index and read pointer position, and read completed or terminated; if the reading is completed or terminated, clear the read start and end information of the "delay telemetry playback setting information" in the simulation status bus.

[0163] (4) Otherwise, read a frame of data at the found pointer position and record it as String strDataRead, and set its read timestamp T delayed_data_read = T sim +Δt, where Δt is the system consumption time in steps 2) and 3) above. Store this frame of data in the data read cache, move the read pointer position backward, and update the read status ReadStatus;

[0164] (5) If the stop running command is not received, jump to 2) to execute the next loop; otherwise, end the operation of this module.

[0165] Since the playback data is periodically collected and framed by the channel time-division multiplexing scheduling control data source simulation model, there is no problem of excessive data traffic at a certain point in time. Therefore, only one frame of data can be read in one cycle of the read loop.

[0166] The present invention proposes a deep space relay link routing spacecraft telemetry simulation architecture. By simulating and operating four types of bus status control information, namely control information, downlink channel simulation status information, data source simulation status information, and solid-state memory read / write control information, the coordination of each model within the system and the operation of the simulation process are realized, so as to simulate the framing of deep space exploration routing spacecraft. The present invention realizes the simulation scheduling of the routing spacecraft downlink channel through the priority dynamic correction algorithm, and controls and manages the time-division multiplexing data sources of the simulation telemetry channels. The present invention realizes the storage, reading, and management of the routing spacecraft simulation telemetry frames through the on-board solid-state memory simulation method, and realizes the generalization definition and access of different types and sources of simulation telemetry frames through the solid-state memory interface protocol and control protocol, supports data query and reading according to time and address, and realizes the simulation of the on-board memory.

[0167] As Figure 6 shown in the following is the structural schematic diagram of a routing spacecraft channel time-division multiplexing telemetry framing simulation device according to an embodiment of the present invention. The device shown in the figure includes:

[0168] A data source simulation module 10, configured to receive simulation data. If the simulation data is the telemetry data of the target spacecraft, the pre-established data source simulation model is called to perform real-time transmission virtual channel data source simulation processing on the simulation data, so as to encapsulate the simulation data into real-time transmission target spacecraft virtual channel data units, and use the pre-established on-board solid-state memory simulation model to perform verification, classification, and storage of the data to be stored according to the status bus information;

[0169] A downlink channel simulation module 20, configured to if the simulation data is simulation operation control command data, call the pre-established downlink channel time-division multiplexing simulation model to perform telemetry framing simulation processing on the simulation data, so as to call the data source simulation model to perform real-time transmission virtual channel data source simulation processing according to the status bus information;

[0170] A telemetry frame module 30, configured to obtain and publish the telemetry frames sent by the downlink channel time-division multiplexing simulation model, and perform simulation time advancement to obtain the telemetry framing simulation result; wherein, the telemetry framing simulation result is used to determine the relay link resource allocation of the on-orbit spacecraft during the execution of the exploration mission.

[0171] As an embodiment of the present invention, as Figure 7 shown, the device further includes:

[0172] An initialization module 40, configured to perform parameter initialization processing according to preset configuration information, and instantiate a downlink channel time-division multiplexing simulation model, a data source simulation model, and an on-board fixed storage simulation model;

[0173] A simulation time module 50, configured to receive the simulation time information of each model sent by the downlink channel time-division multiplexing simulation model, the data source simulation model, and the on-board fixed storage simulation model, and determine the simulation time by using the simulation time information of each model.

[0174] As an embodiment of the present invention, as Figure 8 shown, the device further includes: a parameter update module 60, configured to, if the simulation data is simulation operation control command data, preset to execute the simulation operation control command, the flight program, and the delay instruction, and update the telemetry parameter value.

[0175] Based on the same application concept as the above-mentioned method for simulating the telemetry frame multiplexing of a routing spacecraft channel time-division multiplexing, the present invention also provides the above-mentioned device for simulating the telemetry frame multiplexing of a routing spacecraft channel time-division multiplexing. Since the principle of solving problems by this device for simulating the telemetry frame multiplexing of a routing spacecraft channel time-division multiplexing is similar to that of the method for simulating the telemetry frame multiplexing of a routing spacecraft channel time-division multiplexing, the implementation of this device for simulating the telemetry frame multiplexing of a routing spacecraft channel time-division multiplexing can refer to the implementation of the method for simulating the telemetry frame multiplexing of a routing spacecraft channel time-division multiplexing, and the repeated parts will not be described again.

[0176] The present invention establishes a spacecraft telemetry simulation architecture including a simulation controller, a simulation status bus, a downlink channel time-division multiplexing simulation model, a data source simulation model, and an on-board fixed storage simulation model, simulates the process of framing telemetry data of a routing spacecraft, realizes accurate simulation of the downlink channel framing process of a routing spacecraft under deep space large time delay conditions, and has the ability to provide a simulation environment alone or in cooperation with other models for the scheme demonstration before the implementation of a deep space exploration mission and the flight control software test, ensuring that the spacecraft efficiently and accurately executes the deep space exploration mission and saving resource costs.

[0177] The present invention also provides an electronic device, including a memory, a processor, and a computer program stored on the memory and executable on the processor, and the processor realizes the above method when executing the program.

[0178] The present invention also provides a computer program product, including computer programs / instructions, and the computer programs / instructions realize the steps of the above method when executed by a processor.

[0179] The present invention also provides a computer-readable storage medium, and the computer-readable storage medium stores a computer program for the computer to execute the above method.

[0180] As Figure 9As shown, the electronic device 600 may further include: a communication module 110, an input unit 120, an audio processor 130, a display 160, and a power supply 170. It should be noted that the electronic device 600 does not necessarily have to include Figure 9 all the components shown in; in addition, the electronic device 600 may further include Figure 9 components not shown in, and reference may be made to the prior art.

[0181] As Figure 9 shown, the central processing unit 100, sometimes also referred to as a controller or operation control, may include a microprocessor or other processor device and / or logic device. The central processing unit 100 receives inputs and controls the operations of the various components of the electronic device 600.

[0182] Among them, the memory 140 may be, for example, one or more of a buffer, a flash memory, a hard drive, a removable medium, a volatile memory, a non-volatile memory, or other suitable devices. The above information related to failures can be stored, and in addition, programs for executing relevant information can also be stored. And the central processing unit 100 can execute the programs stored in the memory 140 to implement information storage or processing, etc.

[0183] The input unit 120 provides inputs to the central processing unit 100. The input unit 120 is, for example, a key or a touch input device. The power supply 170 is used to supply power to the electronic device 600. The display 160 is used to display display objects such as images and texts. The display may be, for example, an LCD display, but is not limited thereto.

[0184] The memory 140 may be a solid-state memory, for example, a read-only memory (ROM), a random access memory (RAM), a SIM card, etc. It may also be such a memory that stores information even when powered off, can be selectively erased and has more data stored. Examples of such a memory are sometimes referred to as EPROMs, etc. The memory 140 may also be some other type of device. The memory 140 includes a buffer memory 141 (sometimes referred to as a buffer). The memory 140 may include an application / function storage unit 142, which is used to store application programs and function programs or the processes for operating the electronic device 600 through the central processing unit 100.

[0185] The memory 140 may also include a data storage unit 143, which is used to store data, such as contacts, digital data, pictures, sounds, and / or any other data used by the electronic device. The driver storage unit 144 of the memory 140 may include various drivers of the electronic device for communication functions and / or for performing other functions of the electronic device (such as a messaging application, an address book application, etc.).

[0186] The communication module 110 is a transmitter / receiver 110 that transmits and receives signals via the antenna 111. The communication module (transmitter / receiver) 110 is coupled to the central processor 100 to provide input signals and receive output signals, which may be the same as in the case of a conventional mobile communication terminal.

[0187] Based on different communication technologies, multiple communication modules 110 may be provided in the same electronic device, such as a cellular network module, a Bluetooth module, and / or a wireless local area network module, etc. The communication module (transmitter / receiver) 110 is also coupled to the speaker 131 and the microphone 132 via the audio processor 130 to provide an audio output via the speaker 131 and receive an audio input from the microphone 132, thereby implementing the usual telecommunications functions. The audio processor 130 may include any suitable buffers, decoders, amplifiers, etc. Additionally, the audio processor 130 is also coupled to the central processor 100, so that recording can be performed on the local machine through the microphone 132, and the sound stored on the local machine can be played through the speaker 131.

[0188] Those skilled in the art should understand that the embodiments of the present invention may be provided as a method, a system, or a computer program product. Therefore, the present invention may take the form of a completely hardware embodiment, a completely software embodiment, or an embodiment combining software and hardware aspects. Moreover, the present invention may take the form of a computer program product implemented on one or more computer-usable storage media (including but not limited to disk memory, CD-ROM, optical memory, etc.) that contain computer-usable program code.

[0189] The present invention is described with reference to the flowcharts and / or block diagrams of methods, apparatuses (systems), and computer program products according to embodiments of the present invention. It should be understood that each flow and / or block in the flowcharts and / or block diagrams, and the combination of flows and / or blocks in the flowcharts and / or block diagrams, can be implemented by computer program instructions. These computer program instructions can be provided to the processor of a general-purpose computer, a special-purpose computer, an embedded processor, or other programmable data processing devices to generate a machine, such that the instructions executed by the processor of the computer or other programmable data processing devices generate means for implementing the functions specified in Figure 1 one process or multiple processes and / or blocks Figure 1 one block or multiple blocks.

[0190] These computer program instructions can also be stored in a computer-readable memory that can direct a computer or other programmable data processing device to work in a specific manner, such that the instructions stored in the computer-readable memory generate a manufactured article including instruction means, and the instruction means implement the functions specified in Figure 1 one process or multiple processes and / or blocksFigure 1 The functions specified in one or more boxes.

[0191] These computer program instructions can also be loaded onto a computer or other programmable data processing device, so that a series of operation steps are executed on the computer or other programmable device to generate a computer-implemented process. Thus, the instructions executed on the computer or other programmable device provide for implementing in the process Figure 1 One or more processes and / or boxes Figure 1 The steps of the functions specified in one or more boxes.

[0192] In the present invention, specific embodiments are used to elaborate on the principles and implementation manners of the present invention. The description of the above embodiments is only used to help understand the method and its core idea of the present invention; at the same time, for those of ordinary skill in the art, according to the idea of the present invention, there will be changes in the specific implementation manners and application scopes. In summary, the content of this specification should not be construed as a limitation to the present invention.

Claims

1. A simulation method for time-division multiplexing telemetry framing of a routing spacecraft channel, characterized in that The method comprises: receiving simulation data, and if the simulation data is target spacecraft telemetry data, invoking a pre-established data source simulation model to perform real-time transmission virtual channel data source simulation processing on the simulation data to encapsulate the simulation data into real-time transmission target spacecraft virtual channel data units, and utilizing a pre-established on-board storage simulation model to verify, classify, and store the data to be stored based on state bus information; If the simulation data is simulation operation control command data, a pre-established downlink channel time-division multiplexing simulation model is called to perform telemetry framing simulation processing on the simulation data, so as to call the data source simulation model to perform real-time transmission virtual channel data source simulation processing according to the state bus information; Acquiring and publishing telemetry frames sent by the downlink channel time-division multiplexing simulation model, and performing simulation time advancement to obtain telemetry framing simulation results; wherein the telemetry framing simulation results are used to determine relay link resource allocation for the on-orbit spacecraft during the detection mission execution; The telemetry framing simulation process includes: 1) If , it indicates that the framing time has been reached and telemetry framing starts; 2) Update the most recent telemetry framing time ; Based on priority scheduling, elect the data source that satisfies p cadu [k]=argmax(Prd) as the framing content; 3) If there are m data sources with the same priority, calculate for each data source in turn ; , indicating that the data source has not reached the download time yet, is the time to wait; skip this data; If , its modulus is the lag duration downloaded by the current data source; select the data source k that satisfies as the election result, and add the correction parameter to the priorities of other data sources with the same priority: Among them , it is used to dynamically adjust the priority while avoiding affecting the overall distribution of the priority due to the correction behavior: 4) Execute the cycle judgment of data source k. If T frame -T cadu_recent_frame [k]≥t cadu [k], it means that the data source meets the downlink cycle, and then seizes the channel bandwidth to start downlink; update T cadu_recent_frame [k]=T frame ; 5) If T frame -T cadu_recent_frame [k]<t cadu [k], it indicates that this data source does not meet the download condition; restore its priority to the initial state p cadu [m]=p', and seek the second-priority data to satisfy p cadu [j]=argmax(Prd); j!=k, return to step 3); 6) If the telemetry framing time is reached but all data sources have no available data, fill the channel with filler data; 7) Perform telemetry encapsulation and verification operations, completing one framing process. Return to 1) and execute again.

2. The method according to claim 1, characterized in that The method further comprises: Perform parameter initialization processing according to preset configuration information, and implement the downlink channel time-division multiplexing simulation model, data source simulation model and on-device persistent storage simulation model; Receive simulation time information of each model sent by the downlink channel time-division multiplexing simulation model, the data source simulation model and the on-device persistent storage simulation model, and use the simulation time information of each model to determine the simulation time.

3. A simulation device for time-division multiplexing telemetry framing of a routing spacecraft channel, characterized in that, The device comprises: A data source simulation module is configured to receive simulation data and, if the simulation data is target spacecraft telemetry data, invoke a pre-established data source simulation model to perform real-time transmission virtual channel data source simulation processing on the simulation data to encapsulate the simulation data into real-time transmission target spacecraft virtual channel data units, and utilize a pre-established on-board storage simulation model to verify, classify, and store the data to be stored based on state bus information. a downlink channel simulation module configured to, if the simulation data is simulation operation control command data, call a pre-established downlink channel time-division multiplexing simulation model to perform telemetry framing simulation processing on the simulation data, and to call the data source simulation model to perform real-time transmission virtual channel data source simulation processing based on the status bus information; a telemetry frame module configured to acquire and publish telemetry frames sent by the downlink channel time-division multiplexing simulation model, and perform simulation time advancement to obtain telemetry framing simulation results; wherein the telemetry framing simulation results are used to determine relay link resource allocation for on-orbit spacecraft during the execution of a detection mission; The telemetry framing simulation process includes: 1) If , it indicates that the framing time has arrived and telemetry framing starts; 2) Update the most recent telemetry framing time ; Based on priority scheduling, elect the data source that satisfies p cadu [k]=argmax(Prd) as the framing content; 3) If there are m data sources with the same priority, calculate for each data source in turn ; , indicating that the data source has not reached the download time yet, is the time to wait; skip this data; If , its modulus is the lag duration downloaded by the current data source; select the data source k that satisfies as the election result, and add the correction parameter to the priorities of other data sources with the same priority: Among them , it is used to dynamically adjust the priority while avoiding affecting the overall distribution of the priority due to the correction behavior: 4) Perform a periodic judgment on data source k. If T frame -T cadu_recent_frame [k]≥t cadu [k], it means that this data source meets the download period, and then preempts the channel bandwidth to start downloading; update T cadu_recent_frame [k]=T frame ; 5) If T frame -T cadu_recent_frame [k]<t cadu [k], it indicates that this data source does not meet the download condition; restore its priority to the initial state p cadu [m]=p', and seek the second-priority data to meet p cadu [j]=argmax(Prd); j!=k, return to step 3); 6) If the telemetry framing time is reached but all data sources have no available data, fill the channel with filler data; 7) Perform telemetry encapsulation and verification operations, completing one framing process. Return to 1) and execute again.

4. The device according to claim 3, characterized in that The device also includes: An initialization module, configured to perform parameter initialization processing according to preset configuration information, and instantiate the downlink channel time-division multiplexing simulation model, the data source simulation model, and the on-board solid-state memory simulation model; A simulation time module, configured to receive the simulation time information of each model sent by the downlink channel time-division multiplexing simulation model, the data source simulation model, and the on-board solid-state memory simulation model, and determine the simulation time by using the simulation time information of each model.

5. A routing spacecraft channel time-division multiplexing telemetry framing simulation system that executes the method according to any one of claims 1-2, characterized in that, The system includes: a telemetry simulation controller, a downlink channel time-division multiplexing simulation model, a data source simulation model, an on-board solid-state memory simulation model, and a telemetry simulation status bus; The telemetry simulation controller is configured to receive simulation data. If the simulation data is the telemetry data of the target spacecraft, it calls the pre-established data source simulation model to perform real-time transmission virtual channel data source simulation processing on the simulation data. If the simulation data is the simulation operation control command data, it calls the pre-established downlink channel time-division multiplexing simulation model to perform telemetry framing simulation processing on the simulation data. It acquires and publishes the telemetry frames sent by the downlink channel time-division multiplexing simulation model, and advances the simulation time to obtain the telemetry framing simulation result. Among them, the telemetry framing simulation result is used to determine the relay link resource allocation of the on-orbit spacecraft during the execution of the detection task; The downlink channel time-division multiplexing simulation model is configured to perform downlink channel scheduling according to the current device simulation time and status bus information. If the current channel scheduling result is to route the service data channel of the spacecraft itself, it performs its own service telemetry virtual channel scheduling according to the status bus information of the telemetry simulation status bus, and transfers the scheduling result to the data source simulation model; according to the preset framing code rate, it encapsulates the real-time transmission target spacecraft virtual channel data unit generated by the data source simulation model into a telemetry frame, and performs verification and encoding on the telemetry frame; The data source simulation model is configured to use the scheduling result to judge the virtual channel type, and perform real-time transmission virtual channel data source simulation according to the virtual channel type, encapsulate the simulation data into a real-time transmission target spacecraft virtual channel data unit, and call the on-board solid-state memory simulation model; The on-board solid-state memory simulation model is configured to query the simulation solid-state memory record data according to the data playback range in the telemetry simulation status bus and generate a delayed telemetry reading result for the data source simulation model to generate a delayed telemetry playback virtual channel data unit; according to the status bus information of the telemetry simulation status bus, perform verification, classification, and storage on the real-time transmission target spacecraft virtual channel data unit and the delayed telemetry playback virtual channel data unit.

6. The system according to claim 5, wherein The telemetry simulation controller is further configured to perform parameter initialization processing according to preset configuration information, and instantiate the downlink channel time-division multiplexing simulation model, the data source simulation model, and the on-board solid-state memory simulation model; receive the simulation time information of each model sent by the downlink channel time-division multiplexing simulation model, the data source simulation model, and the on-board solid-state memory simulation model, and determine the simulation time by using the simulation time information of each model.

7. The system according to claim 5, characterized in that The downlink channel time-division multiplexing simulation model is also used to determine the downlink conditions by using the simulation time, spacecraft telemetry framing, the most recent framing time, and the framing period, and perform downlink channel scheduling simulation processing according to the determination result of the downlink conditions.

8. The system according to claim 5, characterized in that, The on-board fixed storage simulation model includes a data playback module, a data writing module, and a storage space module; The data playback module is used to read the corresponding telemetry from the storage space according to the preset playback rules; the data writing module is used to write various virtual channel data units generated by the data source simulation model into the storage space module according to the time, source, and category.

9. An electronic device, comprising a memory, a processor, and a computer program stored on the memory and executable on the processor, characterized in that, When the processor executes the computer program, it implements the method according to any one of claims 1 to 2.

10. A computer-readable storage medium, characterized in that, The computer-readable storage medium stores a computer program for the computer to execute the method according to any one of claims 1 to 2.

Images