A ground flight control and operation and maintenance support system for ultra-low orbit satellite constellations
The ground flight control system for ultra-low orbit satellite constellations, which integrates modules such as attitude and orbit control system simulation modules, solves the problems of real-time orbit control and remote sensing task allocation for ultra-low orbit satellite constellations. It achieves high-precision orbit control and collision avoidance, and improves the safety and intelligence of constellation operation.
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Patents(China)
- Current Assignee / Owner
- SESBEST (SHAOXING) INTELLIGENT TECH CO LTD
- Filing Date
- 2023-11-13
- Publication Date
- 2026-05-26
AI Technical Summary
Existing technologies are insufficient to achieve real-time orbit control, remote sensing task allocation, ground control station telemetry and control information support, and effective forecasting and decision support for orbit collision avoidance of ultra-low orbit satellite constellations. They also suffer from isolated orbit control strategies and insufficient emergency response.
Employing an attitude and orbit control system simulation module, a constellation collaborative control module, a space environment prediction module, a collision avoidance module, and an autonomous mission generation module, combined with database management, it achieves ultra-real-time closed-loop simulation and prediction, generates satellite orbit control strategies and automatically orchestrates missions, and provides real-time data monitoring and future event prediction.
It improves the orbit control accuracy and safety of the ultra-low orbit satellite constellation, ensures the efficient completion of remote sensing missions, provides collision warning and fault identification capabilities, and enhances the intelligence and safety of constellation operation.
Smart Images
Figure CN117585194B_ABST
Abstract
Description
Technical Field
[0001] This invention belongs to the field of aircraft overall design and relates to a ground flight control and operation and maintenance support platform for ultra-low orbit satellite constellations, providing a system solution for satellite flight control and operation and maintenance. Background Technology
[0002] The ultra-low Earth orbit (150km–345km) currently lacks permanently operational satellite deployments, making it a hot area with immense development potential. SuperEarth Observer, a U.S. company, has received an Air Force research and development contract to develop ultra-low Earth orbit application satellites, codenamed "Manta Ray." One of its advantages is its ability to operate in ultra-low Earth orbit, enabling the formation of constellations in space at a relatively low cost. The Air Force Research Laboratory at the Space and Missile Systems Center sees another advantage of the project: "Manta Ray" can provide near-real-time satellite imagery to the U.S. Air Force and Army, transmitting satellite images to ground stations or mobile users within minutes. Denver-based aerospace startup Albedo plans to build a constellation of 24 satellites to achieve high-resolution imaging of visible light ground pixels at 10cm and infrared at 2m.
[0003] While ultra-low Earth orbit (ULE) satellites hold great promise for applications, their application also presents significant technical challenges, primarily including:
[0004] 1) Due to the high aerodynamic drag of ultra-low orbit (ULO) and its constantly changing space environment, for example, SpaceX experienced a geomagnetic storm, resulting in 40 out of 49 Starlink satellites launched on February 3, 2022, re-entering the atmosphere and being destroyed the following day. ULE satellites operate year-round, using electric propulsion for long-term orbital maintenance. Their control strategies are closely related to the space environment, making real-time monitoring of the orbital control strategies of the constellation and the operation and maintenance of the satellites a significant challenge.
[0005] 2) When ultra-low orbit satellites pass over ground tracking and control stations, their pitch angle changes much faster than that of higher orbits. Furthermore, since the satellites are often in the process of orbit control, the range of their nadir position changes is significantly higher than that of traditional medium and low orbit satellites, which greatly increases the uncertainty for ground tracking and control and thus brings risks.
[0006] 3) Ultra-low Earth orbit (ULE) satellites are already subject to significant orbital variations due to atmospheric drag, and they also undergo frequent orbital control. Furthermore, because ULE satellites often require large attitude adjustments during remote sensing imaging, their aerodynamic drag is greater than that of satellites with typically three-axis stable attitudes, thus affecting their orbital decay rate. Maintaining the required orbital control accuracy for ULE satellites is a challenging problem.
[0007] 4) Because they are constantly in the process of changing orbits, the conditions for avoiding collisions with satellites are different from those of traditional satellites, which increases a lot of uncertainty. How to carry out collision avoidance control for ultra-low orbit constellations is a new challenge.
[0008] Conventional methods for ground flight control and maintenance of on-orbit satellites typically include real-time telemetry data monitoring for flight control, mathematical simulation calculations of the scheme, and target aircraft-accompanied verification.
[0009] To support flight control, the most common approaches currently available are as follows:
[0010] Technical Solution 1) Real-time flight control telemetry data monitoring: Determine the flight control status based on the current downlink flight control data;
[0011] Technical Solution 2) Mathematical Simulation Calculation: Using a specific on-orbit operating condition as the initial baseline, mathematical calculations and simulations are performed to obtain simulation results over a period of time. The flight control event status is then evaluated based on the simulation results.
[0012] Technical Solution 3) Target Aircraft Accompanying Verification: Using a certain on-orbit operating condition as the initial benchmark, the target aircraft is run to obtain test data, which is usually verified in advance to obtain data that is closer to the actual on-orbit flight state.
[0013] The existing technical solutions mainly have the following problems:
[0014] The method in 1) can only monitor the real-time status of flight control, but cannot estimate or predict future events in advance.
[0015] 2) Mathematical simulations can predict future states, but they are purely logical operations and differ from actual flight conditions, offering limited assistance in flight control decisions during emergencies. Furthermore, these mathematical simulations are relatively isolated and do not integrate with constellation control or onboard mission implementation for closed-loop management.
[0016] In the target machine accompaniment verification in 3), the method can effectively simulate the in-orbit state that is known in advance, but it cannot verify the state caused by sudden events in a timely manner, and it is difficult to effectively support decision-making. Summary of the Invention
[0017] The technical problem solved by this invention is to overcome the shortcomings of the prior art and provide a ground flight control and operation and maintenance support system for ultra-low orbit satellite constellations. This system can provide satellite orbit control strategies, real-time allocation of constellation remote sensing tasks, ground telemetry and control station telemetry and control information support, and ground verification, forecasting and decision support for orbit collision avoidance during the constellation construction and operation process.
[0018] The technical solution of this invention is: a ground flight control and operation and maintenance support system for ultra-low orbit satellite constellations, comprising:
[0019] Attitude and orbit control system simulation module, one for each satellite; after receiving input data, the attitude and orbit control system simulation module performs ultra-real-time closed-loop simulation to simulate the satellite's status data for the next three days, including the satellite's attitude and orbit data, CMG rotation speed data, battery power data, fuel quality data, and telemetry and control station coverage information;
[0020] The constellation coordination control module receives satellite telemetry information from the telemetry and control station, i.e., the positioning results from the onboard GNSS receiver, determines the orbit, and outputs precise satellite orbit determination data to the attitude and orbit control system simulation module. Simultaneously, the constellation coordination control module receives orbital data and fuel mass data for each satellite from the attitude and orbit control system simulation module, as well as user requirements for the constellation configuration, and performs coordinated control of the constellation configuration, i.e., maintaining orbital altitude, phase, and right ascension of the ascending node, and outputs orbit control commands and constellation relative position maintenance evaluation results. The constellation coordination control module also receives collision risk satellite IDs from the collision avoidance module, as well as TLE data for spacecraft or space debris that may collide with those satellites, performs collision avoidance through phase adjustment, and outputs orbit control commands.
[0021] The space environment forecasting module forecasts space environment information, including solar and geomagnetic indices, and sends it to the attitude and orbit control system simulation module.
[0022] The collision avoidance module receives orbital data for each satellite from the attitude and orbit control system simulation module, as well as TLE data for spacecraft and space debris acquired externally. It calculates the probability of collision between the satellite constellation and other spacecraft or space debris. If there is a collision risk, it outputs the satellite ID and the TLE data of the spacecraft or space debris that are at risk of collision with the satellite to the constellation cooperative control module.
[0023] The autonomous mission generation module receives orbital data and battery power data of each satellite output by the attitude and orbit control system simulation module, as well as user requirements for remote sensing and data transmission missions. It automatically arranges Earth remote sensing and data transmission missions, selects those with observation conditions based on the location of remote sensing points / data transmission stations, generates imaging / data transmission service instructions, and outputs them to the attitude and orbit control system simulation module.
[0024] like Figure 8As shown, the database management module receives attitude and orbit data, CMG rotation speed data, battery power data, and fuel quality data of each satellite output by the attitude and orbit control system simulation module and compares them with the satellite telemetry information obtained by the telemetry and control station. For errors exceeding the threshold, it identifies and locates faults and outputs the comparison results and fault flag bits.
[0025] The input data in the attitude and orbit control system simulation module includes: precise satellite orbit determination data obtained from the constellation collaborative control module, serving as the initial orbit values for the closed-loop simulation; satellite telemetry information obtained from the telemetry and control station, including attitude angle, angular velocity, CMG rotation speed, battery charge, tank pressure, and temperature information, serving as the initial attitude and equipment status values for the closed-loop simulation; space environment information obtained from the space environment prediction module; orbit control commands obtained from the constellation collaborative control module; and imaging / data transmission service commands obtained from the autonomous mission generation module.
[0026] The attitude and orbit control system simulation module includes an initialization submodule, a dynamics submodule, and an on-board attitude and orbit control algorithm submodule. The initialization submodule uses precise satellite orbit determination data obtained from the constellation collaborative control module as the initial orbit value, and obtains satellite telemetry information from the telemetry and control station as the initial attitude and equipment status values, and sends them to the dynamics submodule. The dynamics submodule uses the simulation initial values obtained from the initialization submodule to perform ultra-real-time closed-loop simulation with the on-board attitude and orbit control algorithm submodule. During the closed-loop simulation, the dynamics submodule introduces space environment information obtained from the space environment prediction module, and the attitude and orbit control algorithm submodule introduces orbit control commands obtained from the constellation collaborative control module and imaging / data transmission service commands obtained from the autonomous mission generation module.
[0027] The dynamics submodule uses the HPOP algorithm and incorporates space environment information obtained from the space environment prediction module for high-precision orbit prediction.
[0028] The onboard attitude and orbit control algorithm submodule responds to orbit control commands obtained from the constellation collaborative control module and imaging / data transmission service commands obtained from the autonomous mission generation module. It performs corresponding attitude and orbit maneuver simulations in a closed loop with the dynamics submodule, and outputs satellite attitude and orbit data, CMG rotation speed data, battery power data, fuel quality data, and telemetry and control station coverage information.
[0029] The constellation coordination control module receives user requirements for constellation configuration, including requirements for satellite orbital altitude, relative phase between satellites, and right ascension of the relative ascending node between satellites.
[0030] The constellation coordinated control module includes an orbit determination submodule, an orbit altitude, phase, and ascending node maintenance control submodule, a constellation relative position maintenance evaluation submodule, and an avoidance maneuver submodule. The orbit determination submodule receives satellite telemetry information from the telemetry and control station (TT&C station), i.e., the positioning results from the onboard GNSS receiver, performs orbit determination, and outputs precise satellite orbit determination data to the attitude and orbit control system simulation module. The orbit altitude, phase, and ascending node maintenance control submodule receives orbit data and fuel mass data for each satellite output from the attitude and orbit control system simulation module, as well as user requirements for the constellation configuration, and performs coordinated constellation configuration control, i.e., maintaining orbit altitude, phase, and right ascension of the ascending node, and outputs orbit control commands. The constellation relative position maintenance evaluation submodule receives orbit data for each satellite output from the attitude and orbit control system simulation module, performs constellation phase maintenance evaluation, and outputs the constellation relative position maintenance evaluation result. The avoidance maneuver submodule receives the collision risk satellite IDs and TLE data of spacecraft or space debris that may collide with the satellites from the collision avoidance module, performs collision avoidance through phase adjustment, and outputs orbit control commands.
[0031] The space environment forecasting module forecasts space environment information including solar and geomagnetic indices, including the solar F10.7 index and the geomagnetic Ap / Kp index.
[0032] The collision avoidance module includes an input data preprocessing submodule, various filtering submodules, an SGP4 orbit prediction submodule, an error data calculation submodule, a collision probability calculation submodule, and a risk assessment submodule. The input data preprocessing submodule receives orbit data for each satellite output by the attitude and orbit control system simulation module, as well as TLE data for spacecraft and space debris acquired externally, and performs data preprocessing. The various filtering submodules filter spacecraft and space debris, and the filtered TLE data enters the SGP4 orbit prediction submodule for orbit prediction. The prediction results enter the error data calculation submodule, the collision probability calculation submodule, and the risk assessment submodule to perform prediction error data calculation, collision probability calculation, and risk assessment calculation, respectively, and output the satellite ID with collision risk and the TLE data of the spacecraft or space debris with collision risk to the constellation cooperative control module.
[0033] The autonomous mission generation module receives data output from the attitude and orbit control system simulation module, as well as user requirements for remote sensing and data transmission missions. It automatically arranges the Earth remote sensing and data transmission missions, and generates a series of attitude and orbit adjustment time points and instructions for remote sensing and data transmission missions during satellite flight. The instructions are then output to the attitude and orbit control system simulation module.
[0034] The advantages of this invention compared to the prior art are:
[0035] 1) The ground flight control and operation and maintenance support system for the ultra-low orbit satellite constellation of this invention incorporates the predicted space environment information into the satellite orbit control strategy generation and control implementation monitoring process, which can effectively ensure the safety and operation and maintenance of the constellation satellites;
[0036] 2) The flight control and operation and maintenance support system, due to its higher orbit prediction accuracy, can help ground control stations capture and track satellites to the greatest extent possible during satellite transit.
[0037] 3) The satellite attitude and orbit control system simulation module simulates the effects of attitude control and orbit control on orbital maneuvers in real time, thereby achieving higher orbital maintenance accuracy and providing better assurance for the precise implementation of remote sensing missions for ultra-low orbit constellations.
[0038] 4) Automatic scheduling of Earth remote sensing missions provides a guarantee of speed and effectiveness for the coordinated control of constellation satellites and the efficient completion of application tasks.
[0039] 5) The database management module can automatically identify and handle events with large errors and satellite system faults, making constellation operation and maintenance more intelligent. Furthermore, with the long-term accumulation of data from constellation operation, it creates conditions for the application of artificial intelligence technology in the future.
[0040] 6) Collision warning provides a safety guarantee for the operation of ultra-low orbit constellations. Attached Figure Description
[0041] Figure 1 This is a block diagram of the system modules.
[0042] Figure 2 This diagram illustrates the data input and reception between system modules.
[0043] Figure 3 This is a schematic diagram of the attitude and trajectory control system simulation module.
[0044] Figure 4 This is a schematic diagram of the constellation collaborative control module.
[0045] Figure 5 This is a schematic diagram of the space environment forecasting module.
[0046] Figure 6 This is a schematic diagram of a collision avoidance module.
[0047] Figure 7 This is a schematic diagram of the autonomous task generation module.
[0048] Figure 8 This is a schematic diagram of the database management module. Detailed Implementation
[0049] To make the objectives, technical solutions, and advantages of the present invention clearer, the common embodiments of the present invention will be described in further detail below with reference to the accompanying drawings.
[0050] like Figure 1 , 2 The diagram shows the structural block diagram of the ground flight control and operation and maintenance support system for the ultra-low orbit constellation of the present invention, including:
[0051] Attitude and orbit control system simulation module, one for each satellite; after receiving input data, the attitude and orbit control system simulation module performs ultra-real-time closed-loop simulation to simulate the satellite's status data for the next three days, including the satellite's attitude and orbit data, CMG rotation speed data, battery power data, fuel quality data, and telemetry and control station coverage information;
[0052] The constellation coordination control module receives satellite telemetry information from the telemetry and control station, i.e., the positioning results from the onboard GNSS receiver, determines the orbit, and outputs precise satellite orbit determination data to the attitude and orbit control system simulation module. Simultaneously, the constellation coordination control module receives orbital data and fuel mass data for each satellite from the attitude and orbit control system simulation module, as well as user requirements for the constellation configuration, and performs coordinated control of the constellation configuration, i.e., maintaining orbital altitude, phase, and right ascension of the ascending node, and outputs orbit control commands and constellation relative position maintenance evaluation results. The constellation coordination control module also receives collision risk satellite IDs from the collision avoidance module, as well as TLE data for spacecraft or space debris that may collide with those satellites, performs collision avoidance through phase adjustment, and outputs orbit control commands.
[0053] The space environment forecasting module forecasts space environment information, including solar and geomagnetic indices, and sends it to the attitude and orbit control system simulation module.
[0054] The collision avoidance module receives orbital data for each satellite from the attitude and orbit control system simulation module, as well as TLE data for spacecraft and space debris acquired externally. It calculates the probability of collision between the satellite constellation and other spacecraft or space debris. If there is a collision risk, it outputs the satellite ID and the TLE data of the spacecraft or space debris that are at risk of collision with the satellite to the constellation cooperative control module.
[0055] The autonomous mission generation module receives orbital data and battery power data of each satellite output by the attitude and orbit control system simulation module, as well as user requirements for remote sensing and data transmission missions. It automatically arranges Earth remote sensing and data transmission missions, selects those with observation conditions based on the location of remote sensing points / data transmission stations, generates imaging / data transmission service instructions, and outputs them to the attitude and orbit control system simulation module.
[0056] The database management module receives attitude and orbit data, CMG rotation speed data, battery power data, and fuel quality data of each satellite output by the attitude and orbit control system simulation module and compares them with satellite telemetry information obtained by the telemetry and control station. For errors exceeding the threshold, it identifies and locates faults and outputs the comparison results and fault flag bits.
[0057] The input data in the attitude and orbit control system simulation module includes: precise satellite orbit determination data obtained from the constellation collaborative control module, serving as the initial orbit values for the closed-loop simulation; satellite telemetry information obtained from the telemetry and control station, including attitude angle, angular velocity, CMG rotation speed, battery charge, tank pressure, and temperature information, serving as the initial attitude and equipment status values for the closed-loop simulation; space environment information obtained from the space environment prediction module; orbit control commands obtained from the constellation collaborative control module; and imaging / data transmission service commands obtained from the autonomous mission generation module.
[0058] like Figure 3 As shown, the attitude and orbit control system simulation module includes: an initialization submodule, a dynamics submodule, and an on-board attitude and orbit control algorithm submodule. The initialization submodule uses the satellite's precise orbit determination data obtained from the constellation collaborative control module as the initial orbit value, and obtains satellite telemetry information from the telemetry and control station as the initial attitude value and equipment status value, and sends them to the dynamics submodule. The dynamics submodule uses the simulation initial values obtained from the initialization submodule to perform ultra-real-time closed-loop simulation with the on-board attitude and orbit control algorithm submodule. During the closed-loop simulation, the dynamics submodule introduces space environment information obtained from the space environment prediction module, and the attitude and orbit control algorithm submodule introduces orbit control commands obtained from the constellation collaborative control module and imaging / data transmission service commands obtained from the autonomous mission generation module.
[0059] The dynamics submodule uses the HPOP algorithm and incorporates space environment information obtained from the space environment prediction module for high-precision orbit prediction.
[0060] The onboard attitude and orbit control algorithm submodule responds to orbit control commands obtained from the constellation collaborative control module and imaging / data transmission service commands obtained from the autonomous mission generation module. It performs corresponding attitude and orbit maneuver simulations in a closed loop with the dynamics submodule, and outputs satellite attitude and orbit data, CMG rotation speed data, battery power data, fuel quality data, and telemetry and control station coverage information.
[0061] The constellation coordination control module receives user requirements for constellation configuration, including requirements for satellite orbital altitude, relative phase between satellites, and right ascension of the relative ascending node between satellites.
[0062] like Figure 4As shown, the constellation coordinated control module includes an orbit determination submodule, an orbit altitude, phase, and ascending node maintenance control submodule, a constellation relative position maintenance evaluation submodule, and an avoidance maneuver submodule. The orbit determination submodule receives satellite telemetry information from the telemetry and control station, i.e., the positioning results from the onboard GNSS receiver, performs orbit determination, and outputs precise satellite orbit determination data to the attitude and orbit control system simulation module. The orbit altitude, phase, and ascending node maintenance control submodule receives orbit data and fuel mass data for each satellite output from the attitude and orbit control system simulation module, as well as user requirements for the constellation configuration, and performs coordinated control of the constellation configuration, i.e., maintenance control of orbit altitude, phase, and ascending node right ascension, and outputs orbit control commands. The constellation relative position maintenance evaluation submodule receives orbit data for each satellite output from the attitude and orbit control system simulation module, performs constellation phase maintenance evaluation, and outputs the constellation relative position maintenance evaluation result. The avoidance maneuver submodule receives the collision risk satellite IDs and TLE data of spacecraft or space debris that may collide with the satellites output from the collision avoidance module, performs collision avoidance through phase adjustment, and outputs orbit control commands.
[0063] like Figure 5 As shown, the space environment forecasting module forecasts space environment information including solar and geomagnetic indices, including the solar F10.7 index and the geomagnetic Ap / Kp index.
[0064] like Figure 6 As shown, the collision avoidance module includes an input data preprocessing submodule, various filtering submodules, an SGP4 orbit prediction submodule, an error data calculation submodule, a collision probability calculation submodule, and a risk assessment submodule. The input data preprocessing submodule receives orbit data for each satellite output by the attitude and orbit control system simulation module, as well as TLE data for spacecraft and space debris acquired externally, and performs data preprocessing. The various filtering submodules filter spacecraft and space debris, and the filtered TLE data enters the SGP4 orbit prediction submodule for orbit prediction. The prediction results enter the error data calculation submodule, the collision probability calculation submodule, and the risk assessment submodule to perform prediction error data calculation, collision probability calculation, and risk assessment calculation, respectively, and output the satellite ID with collision risk and the TLE data of the spacecraft or space debris with collision risk to the constellation cooperative control module.
[0065] like Figure 7 As shown, the autonomous mission generation module receives the output data from the attitude and orbit control system simulation module, as well as the user's requirements for remote sensing and data transmission missions. It automatically arranges the Earth remote sensing and data transmission missions, and generates a series of attitude and orbit adjustment time points and instructions for remote sensing and data transmission missions during satellite flight. The instructions are then output to the attitude and orbit control system simulation module.
[0066] Although the present invention has been disclosed above with reference to preferred embodiments, it is not intended to limit the present invention. Any person skilled in the art can make possible changes and modifications to the technical solutions of the present invention based on the above-disclosed technical content without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and modifications made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solutions of the present invention shall fall within the protection scope of the technical solutions of the present invention.
Claims
1. A ground flight control and operation and maintenance support system for an ultra-low Earth orbit satellite constellation, characterized in that, include: Attitude and orbit control system simulation module, one attitude and orbit control system simulation module is configured for each satellite; After receiving the input data, the attitude and orbit control system simulation module performs ultra-real-time closed-loop simulation to obtain the satellite's status data for the next three days, including the satellite's attitude and orbit data, CMG rotation speed data, battery power data, fuel quality data, and telemetry and control station coverage information. The constellation coordination control module receives satellite telemetry information from the telemetry and control station, i.e., the positioning results from the onboard GNSS receiver, determines the orbit, and outputs precise satellite orbit determination data to the attitude and orbit control system simulation module. Simultaneously, the constellation coordination control module receives orbital data and fuel mass data for each satellite from the attitude and orbit control system simulation module, as well as user requirements for the constellation configuration, and performs coordinated control of the constellation configuration, i.e., maintaining orbital altitude, phase, and right ascension of the ascending node, and outputs orbit control commands and constellation relative position maintenance evaluation results. The constellation coordination control module also receives collision risk satellite IDs from the collision avoidance module, as well as TLE data for spacecraft or space debris that may collide with those satellites, performs collision avoidance through phase adjustment, and outputs orbit control commands. The space environment forecasting module forecasts space environment information, including solar and geomagnetic indices, and sends it to the attitude and orbit control system simulation module. The collision avoidance module receives orbital data for each satellite from the attitude and orbit control system simulation module, as well as TLE data for spacecraft and space debris acquired externally. It calculates the probability of collision between the satellite constellation and other spacecraft or space debris. If there is a collision risk, it outputs the satellite ID and the TLE data of the spacecraft or space debris that are at risk of collision with the satellite to the constellation cooperative control module. The autonomous mission generation module receives orbital data and battery power data of each satellite output by the attitude and orbit control system simulation module, as well as user requirements for remote sensing and data transmission missions. It automatically arranges Earth remote sensing and data transmission missions, selects those with observation conditions based on the location of remote sensing points / data transmission stations, generates imaging / data transmission service instructions, and outputs them to the attitude and orbit control system simulation module. The database management module receives attitude and orbit data, CMG rotation speed data, battery power data, and fuel quality data of each satellite output by the attitude and orbit control system simulation module and compares them with satellite telemetry information obtained by the telemetry and control station. For errors exceeding the threshold, it identifies and locates faults and outputs the comparison results and fault flag bits.
2. The ultra-low orbit satellite constellation ground flight control and operation and maintenance support system according to claim 1, characterized in that, The input data in the attitude and orbit control system simulation module includes: precise satellite orbit determination data obtained from the constellation collaborative control module, serving as the initial orbit values for the closed-loop simulation; satellite telemetry information obtained from the telemetry and control station, including attitude angle, angular velocity, CMG rotation speed, battery charge, tank pressure, and temperature information, serving as the initial attitude and equipment status values for the closed-loop simulation; space environment information obtained from the space environment prediction module; orbit control commands obtained from the constellation collaborative control module; and imaging / data transmission service commands obtained from the autonomous mission generation module.
3. The ultra-low orbit satellite constellation ground flight control and operation and maintenance support system according to claim 2, characterized in that, The attitude and orbit control system simulation module includes an initialization submodule, a dynamics submodule, and an on-board attitude and orbit control algorithm submodule. The initialization submodule uses precise satellite orbit determination data obtained from the constellation collaborative control module as the initial orbit value, and obtains satellite telemetry information from the telemetry and control station as the initial attitude and equipment status values, and sends them to the dynamics submodule. The dynamics submodule uses the simulation initial values obtained from the initialization submodule to perform ultra-real-time closed-loop simulation with the on-board attitude and orbit control algorithm submodule. During the closed-loop simulation, the dynamics submodule introduces space environment information obtained from the space environment prediction module, and the attitude and orbit control algorithm submodule introduces orbit control commands obtained from the constellation collaborative control module and imaging / data transmission service commands obtained from the autonomous mission generation module.
4. The ultra-low orbit satellite constellation ground flight control and operation and maintenance support system according to claim 3, characterized in that, The dynamics submodule uses the HPOP algorithm and incorporates space environment information obtained from the space environment prediction module for high-precision orbit prediction.
5. A ground flight control and operation and maintenance support system for an ultra-low orbit satellite constellation according to claim 3, characterized in that, The onboard attitude and orbit control algorithm submodule responds to orbit control commands obtained from the constellation collaborative control module and imaging / data transmission service commands obtained from the autonomous mission generation module. It performs corresponding attitude and orbit maneuver simulations in a closed loop with the dynamics submodule, and outputs satellite attitude and orbit data, CMG rotation speed data, battery power data, fuel quality data, and telemetry and control station coverage information.
6. The ultra-low orbit satellite constellation ground flight control and operation and maintenance support system according to claim 1, characterized in that, The constellation coordination control module receives user requirements for constellation configuration, including requirements for satellite orbital altitude, relative phase between satellites, and right ascension of the relative ascending node between satellites.
7. The ultra-low orbit satellite constellation ground flight control and operation and maintenance support system according to claim 1, characterized in that, The constellation coordinated control module includes an orbit determination submodule, an orbit altitude, phase, and ascending node maintenance control submodule, a constellation relative position maintenance evaluation submodule, and an avoidance maneuver submodule. The orbit determination submodule receives satellite telemetry information from the telemetry and control station (TT&C station), i.e., the positioning results from the onboard GNSS receiver, performs orbit determination, and outputs precise satellite orbit determination data to the attitude and orbit control system simulation module. The orbit altitude, phase, and ascending node maintenance control submodule receives orbit data and fuel mass data for each satellite output from the attitude and orbit control system simulation module, as well as user requirements for the constellation configuration, and performs coordinated constellation configuration control, i.e., maintaining orbit altitude, phase, and right ascension of the ascending node, and outputs orbit control commands. The constellation relative position maintenance evaluation submodule receives orbit data for each satellite output from the attitude and orbit control system simulation module, performs constellation phase maintenance evaluation, and outputs the constellation relative position maintenance evaluation result. The avoidance maneuver submodule receives the collision risk satellite IDs and TLE data of spacecraft or space debris that may collide with the satellites from the collision avoidance module, performs collision avoidance through phase adjustment, and outputs orbit control commands.
8. The ultra-low orbit satellite constellation ground flight control and operation and maintenance support system according to claim 1, characterized in that, The space environment forecasting module forecasts space environment information including solar and geomagnetic indices, including the solar F10.7 index and the geomagnetic Ap / Kp index.
9. A ground flight control and operation and maintenance support system for an ultra-low orbit satellite constellation according to claim 1, characterized in that, The collision avoidance module includes an input data preprocessing submodule, a filtering submodule, an SGP4 orbit prediction submodule, an error data calculation submodule, a collision probability calculation submodule, and a risk assessment submodule. The input data preprocessing submodule receives orbital data for each satellite output by the attitude and orbit control system simulation module, as well as TLE data of spacecraft and space debris acquired externally, and performs data preprocessing. Each screening submodule filters spacecraft and space debris. The selected TLE data enters the SGP4 orbit prediction submodule for orbit prediction. The prediction results enter the error data calculation submodule, collision probability calculation submodule, and risk assessment submodule to calculate prediction error data, collision probability, and risk assessment, respectively. The system outputs the satellite ID with collision risk, the TLE data of the spacecraft or space debris with collision risk to the constellation collaborative control module.
10. A ground flight control and operation and maintenance support system for an ultra-low orbit satellite constellation according to claim 1, characterized in that, The autonomous mission generation module receives data output from the attitude and orbit control system simulation module, as well as user requirements for remote sensing and data transmission missions. It automatically arranges the Earth remote sensing and data transmission missions, and generates a series of attitude and orbit adjustment time points and instructions for remote sensing and data transmission missions during satellite flight. The instructions are then output to the attitude and orbit control system simulation module.