Earth-moon space navigation satellite orbit maintaining system

Abstract

The invention provides an earth-moon space navigation satellite orbit maintenance system, which comprises an acquisition unit, a control unit and an execution unit, and is characterized in that the acquisition unit is configured to acquire state information of a satellite and send the state information to the control unit, and the state information at least comprises orbit information of the satellite; the control unit is configured to receive the state information, calculate propulsion parameters required by orbit maintenance in combination with the state information and a target state required by a satellite, generate a control instruction according to the propulsion parameters, and send the control instruction to the execution unit; and the execution unit comprises a magnetic plasma power propulsion module and is configured to receive the control instruction and adjust the satellite state according to the control instruction, including adjusting the orbit of the satellite. The system has the advantages of stable satellite state improvement, longer satellite service life, finer satellite state adjustment and the like.

Description

Technical Field

[0001] The present invention mainly relates to the field of satellite navigation technology, and in particular to an orbit maintenance system for a terrestrial-lunar space navigation satellite. Background Art

[0002] The orbital accuracy of navigation satellites is crucial for ensuring the accuracy of their navigation signals. Currently, mainstream navigation satellite orbit maintenance systems generally use chemical propulsion, relying on instantaneous high thrust to achieve orbital corrections. While chemical propulsion systems offer the advantages of high thrust and rapid adjustments, they have significant limitations when operating in non-Keplerian orbits, such as the Earth-Moon triplet NRHO orbit.

[0003] First, the high thrust characteristics of chemical propulsion systems during orbital adjustments can easily cause significant attitude disturbances, which in turn affect orbital stability. This drawback is particularly severe for navigation satellites. Excessive thrust not only interferes with the satellite's attitude but also reduces orbital accuracy, ultimately leading to a decrease in navigation signal quality and impacting the availability of satellite services. Second, chemical propulsion systems have low propulsion efficiency and require a large amount of fuel. This not only significantly increases launch costs but also limits the satellite's on-orbit lifespan. Finally, in complex gravitational environments (such as Earth-Moon libration point orbits, which are affected by multiple gravitational sources such as the Earth and the Moon), chemical propulsion systems struggle to achieve high-frequency and precise thrust adjustments. This is especially true in specialized orbits such as Halo and NRHO orbits, where the complex gravitational environment and frequent orbital changes make chemical propulsion even more difficult to meet the requirements for continuous orbit maintenance. Summary of the Invention

[0004] The technical problem to be solved by the present invention is to provide an orbit maintenance system for Earth-Moon space navigation satellites, which has the advantages of improved stability of satellite status, longer satellite life, and more precise satellite status adjustment.

[0005] To solve the above technical problems, the present invention provides an Earth-Moon space navigation satellite orbit maintenance system, comprising: an acquisition unit, wherein the acquisition unit is configured to acquire status information of the satellite and send the status information to a control unit, wherein the status information at least includes the orbit information of the satellite; a control unit, wherein the control unit is configured to receive the status information, calculate the propulsion parameters required for orbit maintenance in combination with the status information and the target state required by the satellite, and generate control instructions based on the propulsion parameters, and send the control instructions to an execution unit; an execution unit, wherein the execution unit includes a magnetoplasma propulsion module, and the execution unit is configured to receive the control instructions and adjust the satellite status according to the control instructions, including adjusting the orbit of the satellite.

[0006] Optionally, the acquisition unit includes one or more of the following acquisition modules, wherein the acquisition module includes a simulated sun sensor, a star sensor, a fiber optic gyroscope, an inertial navigation combination, and a high-precision accelerometer.

[0007] Optionally, the control unit includes one or more of the following control subunits, including a posture control subunit, a track control subunit, a power control subunit and a hardware drive subunit.

[0008] Optionally, the control unit adopts a closed-loop control method, continuously or periodically collecting the status information of the satellite through the collection unit for multiple times, and performs propulsion parameter calculation and control instruction generation in real time.

[0009] Optionally, the maximum thrust generated by the magnetoplasma propulsion module is less than 50 mN.

[0010] Optionally, the magnetoplasma propulsion module is equipped with a transformer, through which a small current thrust output is achieved, and the current intensity is less than 10A.

[0011] Optionally, the execution unit further includes a power processing module, which is configured to be connected to the magnetic plasma propulsion module, receive the control instructions, and provide the power required for orbital propulsion.

[0012] Optionally, the execution unit further includes a propellant storage and supply module, which is configured to be connected to the magnetoplasma propulsion module to provide propellant.

[0013] Optionally, the execution unit includes at least two groups of the magnetoplasma propulsion modules, at least one of which is a backup propulsion module.

[0014] Optionally, the execution unit further includes a reaction flywheel module and a magnetic torquer module, and the reaction flywheel module and the magnetic torquer module are respectively connected to the control unit.

[0015] Compared with the existing technology, the present invention has the following advantages: 1. Satellite status improvement and stability: The use of MPDT propulsion avoids the attitude disturbance problem caused by high thrust in chemical propulsion, thereby maintaining high-precision stability of the orbit and ensuring the accuracy of the navigation signal. 2. Longer satellite life: The MPDT propulsion system has high specific impulse characteristics, higher propulsion efficiency, and significantly reduced fuel consumption. Compared with traditional chemical propulsion, the electric propulsion system can greatly reduce fuel consumption, extend the on-orbit life of the satellite, and achieve long-term and stable navigation services. 3. More precise satellite status adjustment: In complex gravitational environments such as the Earth-Moon Tribody, frequent and subtle orbit adjustments are achieved through the electric propulsion system to ensure that the navigation satellite maintains a precise position on a complex orbit and meets the needs of high-frequency orbit maintenance. BRIEF DESCRIPTION OF THE DRAWINGS

[0016] The accompanying drawings are included to provide a further understanding of the present application. They are incorporated into and constitute a part of this application. The accompanying drawings illustrate embodiments of the present application and, together with this specification, serve to explain the principles of the present application. In the accompanying drawings:

[0017] Figure 1 It is a schematic structural diagram of a cis-lunar space navigation satellite orbit maintenance system according to an embodiment of the present invention. DETAILED DESCRIPTION

[0018] To more clearly illustrate the technical solutions of the embodiments of this application, the following is a brief introduction to the drawings required for describing the embodiments. Obviously, the drawings described below are merely examples or embodiments of this application. Those skilled in the art can apply this application to other similar scenarios based on these drawings without inventive effort. Unless otherwise apparent from the context or otherwise noted, the same reference numerals in the figures represent the same structure or operation.

[0019] As used in this application and the claims, unless the context clearly indicates otherwise, the words "a," "an," "an," and / or "the" are not intended to refer to the singular but may include the plural. Generally speaking, the terms "comprises" and "include" only indicate the inclusion of the steps and elements specifically identified, and these steps and elements do not constitute an exclusive list. A method or apparatus may also include other steps or elements.

[0020] Figure 1 This is a schematic diagram of the structure of a cis-lunar space navigation satellite orbit maintenance system according to an embodiment of the present invention, with reference to Figure 1As shown, it includes: an acquisition unit, which is configured to collect status information of the satellite and send the status information to a control unit, wherein the status information at least includes orbit information of the satellite; a control unit, which is configured to receive the status information, calculate the propulsion parameters required for orbit maintenance in combination with the status information and the target state required by the satellite, and generate control instructions according to the propulsion parameters, and send the control instructions to an execution unit; an execution unit, which includes a magnetoplasma propulsion module, and the execution unit is configured to receive the control instructions and adjust the satellite status according to the control instructions, including adjusting the satellite's orbit.

[0021] In this embodiment, the acquisition unit, control unit, and execution unit are generally interconnected via an onboard bus, forming a tightly coupled satellite orbit maintenance system. The relationship between these units can be described as a process of acquisition (or measurement) - calculation - execution, ensuring the stability and accuracy of the satellite orbit maintenance system. The acquisition unit collects external environmental data and satellite status data, providing real-time status information, including satellite orbit information. The control unit controls and adjusts the satellite status based on the collected data. The control unit calculates the propulsion parameters (or adjustment parameters) required for the desired satellite based on the collected data, generates, and outputs control instructions. The execution unit then receives the control instructions and adjusts the satellite status, including the satellite's orbit, based on the instructions.

[0022] The magnetoplasma propulsion module (MPDT) uses superconducting magnets to generate a magnetic field, which interacts with the plasma current to generate a Lorentz force to generate thrust. The MPDT consists of superconducting magnets, plasma accelerators, thrust vector control, etc. Its thrust direction and magnitude can be flexibly adjusted according to the requirements of orbital control instructions to ensure that the satellite can move along the desired trajectory. As the core of the execution unit, the MPDT uses the interaction between magnetic fields and plasma to generate thrust. The typical specific impulse can reach 5000 seconds, which is much higher than that of chemical propulsion systems. This means that with the same propellant consumption, electric propulsion can provide a higher speed increment, making the orbit maintenance system more fuel-efficient in long-term missions.

[0023] In one example, the acquisition unit includes one or more of the following acquisition modules: a simulated sun sensor, a star sensor, a fiber optic gyroscope, an inertial navigation system, and a high-precision accelerometer. These acquisition modules enable the acquisition unit to collect satellite status information, such as attitude, orbit, and acceleration, individually or in combination.

[0024] For example, a simulated sun sensor collects the position of the sun relative to the satellite, assists in attitude measurement, and helps the attitude controller determine the orientation of the satellite. A star sensor determines the attitude of a satellite by observing the starry sky. Star sensors provide high-precision attitude information and are important equipment for attitude measurement. Fiber optic gyroscopes provide high-dynamic-precision attitude change information by measuring angular velocity, and are often used to compensate for the deficiencies of star sensors in short-term dynamic processes. The inertial navigation combination includes accelerometers and gyroscopes, which are used to measure the acceleration and angular velocity of the satellite in real time. The orbit and attitude state of the satellite are estimated using inertial navigation data. High-precision accelerometers can accurately measure the external forces and accelerations acting on the satellite, helping the control unit understand the current state of motion and make compensations.

[0025] These sensors transmit collected data to the control unit via an onboard bus, providing key information such as satellite attitude, orbital status, and acceleration. Sensors can integrate multi-source information through data fusion to improve data accuracy and robustness. For example, star sensors and fiber-optic gyroscopes are combined for long-term stable measurements and short-term dynamic change perception, while inertial navigation systems provide redundant information.

[0026] In one example, the control unit includes one or more of the following control subunits, including a posture control subunit, a trajectory control subunit, a power control subunit, and a hardware drive subunit.

[0027] For example, the attitude control subunit is responsible for adjusting and controlling the attitude of the satellite to ensure that the propulsion direction and attitude stability meet the mission requirements. It is controlled based on attitude acquisition data (such as star sensors and sun sensors). The orbit control subunit realizes the precise correction and maintenance of the satellite orbit. This control subunit calculates the required propulsion force based on the current orbital state of the satellite and uses MPDT to adjust the orbit. The power control subunit is responsible for managing the power distribution between the execution unit and other payload units of the satellite to ensure a stable power supply during the propulsion process and does not affect the normal operation of other payloads. The hardware driver subunit communicates directly with the hardware through the actuator and is responsible for the actual hardware operations, such as controlling the ignition of the thrusters and executing attitude adjustment instructions.

[0028] In one example, the control unit uses a closed-loop control method, continuously or periodically collecting satellite status information through the acquisition unit, and performing real-time propulsion parameter calculations and control command generation. The relationship between the various units of the orbit maintenance system in this embodiment can be described as a process of acquisition (or measurement) - calculation - execution - feedback. The orbit maintenance system continuously measures the current status through sensors, performing real-time error analysis and adjustments to ensure that the satellite remains in the desired orbit and attitude. This closed-loop feedback system ensures the high precision and reliability of the orbit maintenance system, enabling it to cope with interference from complex space environments and achieve stable orbit and attitude control.

[0029] In one example, the maximum thrust generated by the magnetoplasma propulsion module is less than 50 mN. This embodiment adopts a continuous low-thrust propulsion control method. Through a rationally structured system distribution and coordinated operation between components, it ensures that the electric track maintenance system can achieve long-term stable orbit control and attitude adjustment on orbit.

[0030] MPDT provides continuous low thrust, which is particularly suitable for tasks involving gradual adjustments to orbits. Compared with intermittent high-thrust propulsion, continuous low thrust can reduce attitude disturbances when achieving orbit adjustments, avoid frequent attitude adjustments, and maintain the stability of the satellite system.

[0031] In one example, the magnetoplasma propulsion module is equipped with a transformer, which realizes low-current thrust output with a current intensity of less than 10A.

[0032] In the aerospace field, the development of high-specific impulse and high-thrust electric propulsion systems is crucial for improving spacecraft performance. However, as electric propulsion systems pursue higher thrust and specific impulse, power demands continue to increase, leading to the problem of high power. When transmitting the same power, current and voltage are inversely proportional. According to the power formula P = UI, where P is power, U is voltage, and I is current. When electric propulsion systems require high power operation, using a low-voltage, high-current mode can lead to numerous problems. For example, high currents can significantly increase resistance losses in transmission lines, dissipating a large amount of electrical energy as heat, reducing energy efficiency and causing line overheating, impacting system stability and safety. High currents can also generate electromagnetic interference in electronic equipment, affecting its normal operation. This embodiment reduces current by boosting the voltage on the satellite. Based on the law of electromagnetic induction, the voltage is increased by using a boost device on the satellite (such as a boost transformer) by changing the turns ratio of the primary and secondary coils, making the voltage output of the secondary coil higher than the voltage input of the primary coil. Under the premise of constant power, the voltage is increased, and the current is correspondingly reduced, achieving a low-current, low-thrust output.

[0033] In one example, the execution unit also includes a power processing module, which is configured to connect to the magnetoplasma propulsion module, receive control commands, and provide the power required for orbital propulsion. The power processing module (PPU) is connected between the MPDT and the power control subunit to ensure stable operation of the MPDT within a 10kW power consumption range.

[0034] In one example, the execution unit further includes a propellant storage and supply module, which is configured to connect to the magnetoplasma propulsion module to provide propellant. Exemplarily, the propellant storage and supply module provides the necessary xenon propellant to maintain long-term, stable operation of the orbit maintenance system.

[0035] In one example, the execution unit includes at least two sets of magnetoplasma propulsion modules, at least one of which serves as a backup propulsion module. The key MPDT component in this embodiment features a redundant design, allowing the orbit maintenance system to switch to the backup device in the event of a failure. Of course, other components, such as sensors in the acquisition unit, can also feature redundant designs, though these are not listed here. This provides a multi-level fault-tolerance mechanism, ensuring that the orbit maintenance system can maintain normal satellite operation even if any critical control component experiences a problem.

[0036] In one example, the execution unit further includes a reaction flywheel module and a magnetic torquer module, each of which is connected to the control unit. For example, upon receiving a control instruction, the hardware driver drives the MPDT to provide a small thrust to achieve orbit adjustment, while simultaneously executing attitude adjustment instructions using the reaction flywheel and other components.

[0037] In one example, the operation process of the satellite orbit maintenance system of this embodiment mainly includes: 1. Data input acquisition: various sensors in the acquisition unit acquire information such as attitude, orbit and acceleration, and transmit it to the control unit through the on-board bus. 2. Error calculation and control instruction generation: the control unit generates specific attitude and orbit adjustment control instructions by calculating the deviation. The control unit converts these instructions into specific thrust control and attitude adjustment instructions. 3. Instruction execution: the hardware driver receives the control instruction, drives the MPDT to provide a small thrust to achieve orbit adjustment, and can also use the reaction flywheel to execute the attitude adjustment instruction at the same time. 4. Feedback closed loop: the acquisition unit continuously collects the current status through the sensor, and performs error analysis and adjustment in real time to ensure that the satellite remains on the desired orbit and attitude. This closed loop form ensures that the orbit maintenance system has high precision and high reliability, can cope with complex space environment interference, and achieve stable orbit and attitude control.

[0038] In this embodiment, the satellite orbit maintenance system can adopt a modular design. Its primary advantage lies in the fact that each unit or module is connected via a standard interface (such as an onboard bus), enhancing the flexibility and scalability of the orbit maintenance system. This design also facilitates maintenance and replacement. If a unit, subunit, or module fails, it can be quickly replaced without affecting the entire orbit maintenance system. This highly integrated design reduces the overall system weight and footprint, facilitating overall satellite design.

[0039] The orbit maintenance system for the Earth-Moon space navigation satellite of this embodiment has the following advantages, including: 1. Improved and stable satellite status: The use of MPDT propulsion avoids the attitude disturbance problem caused by high thrust in chemical propulsion, thereby maintaining high-precision stability of the orbit and ensuring the accuracy of the navigation signal. 2. Longer satellite life: The MPDT propulsion system has high specific impulse characteristics, higher propulsion efficiency, and significantly reduced fuel consumption. Compared with traditional chemical propulsion, the electric propulsion system can significantly reduce fuel consumption, extend the on-orbit life of the satellite, and achieve long-term, stable navigation services. 3. More precise satellite status adjustment: In complex gravitational environments such as the Earth-Moon trisolar system, frequent and subtle orbit adjustments are achieved through the electric propulsion system to ensure that the navigation satellite maintains a precise position on a complex orbit and meets high-frequency orbit maintenance requirements.

[0040] Taking the use of lunar navigation satellites in NRHO orbits as an example, their application in near-rectilinear halo orbits (NRHOs) is crucial for future lunar exploration and base construction. NRHOs are stable orbits around the Moon-Earth gravitational equilibrium point, commonly used for deep space exploration missions, lunar-orbiting space stations, and future lunar navigation satellite systems. NRHO orbits offer the following characteristics: high stability, maintaining a relatively stable lunar orbit for extended periods, making them suitable for long-term missions; and efficient coverage, enabling long-term visibility of the lunar polar regions, facilitating exploration and communication coverage of the lunar north and south poles.

[0041] Although the NRHO orbit is relatively stable, it is still affected by various disturbances, including the gravitational disturbance of the Earth-Moon system, the gravitational influence of the Sun, and the solar radiation pressure. These disturbances can cause the satellite to gradually deviate from the designed orbit, requiring frequent orbit corrections to keep the satellite in the target orbit. The system of this embodiment can provide a continuous small thrust for accurately compensating for orbital disturbances. The high specific impulse (5000 seconds) is very suitable for reducing propellant consumption in missions that require long-term orbit maintenance. The small and continuous thrust provided by the MPDT thruster can smoothly adjust the satellite orbit without causing significant attitude disturbances. This is particularly important for missions such as lunar navigation satellites that require continuous high-precision positioning services. The control unit can automatically determine the orbit deviation and make thrust adjustments based on data provided by sensors such as high-precision accelerometers and star sensors, thereby ensuring that the navigation satellite always remains on the designed NRHO orbit.

[0042] A key characteristic of NRHO orbits is their periodic variations, requiring navigation satellites to regularly make small orbital adjustments to ensure orbital stability. Using this embodiment, the control unit enables navigation satellites to autonomously monitor their orbital status and adjust thrust magnitude and direction according to a predetermined orbital adjustment plan to perform orbital corrections. This autonomous capability eliminates the need for satellites to frequently rely on ground stations for control, significantly reducing the complexity of ground operations.

[0043] Lunar navigation satellites in NRHO orbits need to provide continuous and stable navigation signal coverage of the lunar surface, especially coverage of the lunar polar regions and near the landing site. Using the system of this embodiment, during the orbit adjustment process, the navigation satellite needs to keep its antenna pointing towards the lunar surface to ensure effective coverage of the navigation signal. Through the attitude controller and hardware driver in the onboard closed-loop control system, the satellite can accurately control its attitude while adjusting its orbit, ensuring that the direction of the signal broadcast by the navigation RNSS antenna does not shift, and maintaining continuous coverage of the navigation signal. Since the electric propulsion system requires higher power (about 10kW), the power management system coordinates the power distribution during propulsion with the power demand of the communication payload to ensure the stability of the navigation signal during the orbit adjustment process. This power optimization can achieve the dual functions of propulsion and navigation with limited power resources.

[0044] In the NRHO orbit, it is relatively far away from the earth, and reliance on ground control will lead to signal delays and increased costs. Using the system of this embodiment, the lunar navigation satellite can achieve autonomous control of its orbit and attitude, reduce the frequency of ground station operations, and greatly improve the autonomy and response speed of the mission. Lunar navigation satellites need to provide navigation signals to the lunar surface in a long-term and stable manner. The low-thrust electric propulsion in the NRHO orbit can smoothly perform orbit corrections, reduce the attitude disturbances caused by the orbit maintenance process, and enable the navigation antenna to point more stably at the moon, improving the quality and stability of signal coverage. The long-term maintenance and precise position maintenance of the NRHO orbit place high demands on the efficiency of the propellant. Using the system of this embodiment, the MPDT has high specific impulse characteristics, which can significantly reduce the use of propellant in long-term missions, thereby increasing the on-orbit life of the satellite and providing a larger space for propellant reserves for subsequent missions.

[0045] The basic concepts have been described above. It will be apparent to those skilled in the art that the above disclosures are merely illustrative and do not constitute limitations on this application. Although not explicitly stated herein, those skilled in the art may make various modifications, improvements, and amendments to this application. Such modifications, improvements, and amendments are suggested in this application and remain within the spirit and scope of the exemplary embodiments of this application.

[0046] Some aspects of the present application can be performed entirely by hardware, entirely by software (including firmware, resident software, microcode, etc.), or by a combination of hardware and software. The above hardware or software can be referred to as "data blocks", "modules", "engines", "units", "components" or "systems". The processor can be one or more application-specific integrated circuits (ASICs), digital signal processors (DSPs), digital signal processing devices (DAPDs), programmable logic devices (PLDs), field programmable gate arrays (FPGAs), processors, controllers, microcontrollers, microprocessors or combinations thereof. In addition, various aspects of the present application may be expressed as computer products located in one or more computer-readable media, which include computer-readable program code. For example, computer-readable media may include, but are not limited to, magnetic storage devices (e.g., hard disks, floppy disks, tapes...), optical disks (e.g., compact disks CDs, digital versatile disks DVDs...), smart cards, and flash memory devices (e.g., cards, sticks, key drives...).

[0047] Similarly, it should be noted that, in order to simplify the presentation of this application and thus facilitate understanding of one or more embodiments of the invention, the foregoing descriptions of the embodiments of this application sometimes combine multiple features into a single embodiment, figure, or description thereof. However, this disclosure method does not mean that the subject matter of this application requires more features than those recited in the claims. In fact, an embodiment may have fewer features than all of the features of a single embodiment disclosed above.

[0048] Although the present application has been described with reference to the current specific embodiments, ordinary technicians in this technical field should recognize that the above embodiments are only used to illustrate the present application, and various equivalent changes or substitutions can be made without departing from the spirit of the present application. Therefore, as long as the changes and modifications to the above embodiments are within the scope of the essential spirit of the present application, they will fall within the scope of the claims of the present application.

Claims

1. A cis-lunar space navigation satellite orbit maintenance system, characterized in that: include: a collecting unit, the collecting unit being configured to collect status information of the satellite and send the status information to a control unit, wherein the status information at least includes orbit information of the satellite; a control unit configured to receive the state information, calculate propulsion parameters required for orbit maintenance by combining the state information with a target state required by the satellite, generate a control instruction based on the propulsion parameter, and send the control instruction to an execution unit; An execution unit includes a magnetoplasma propulsion module, and is configured to receive the control instruction and adjust the satellite state according to the control instruction, including adjusting the orbit of the satellite.

2. The cis-lunar space navigation satellite orbit maintenance system according to claim 1, characterized in that: The acquisition unit includes one or more of the following acquisition modules, wherein the acquisition module includes a simulated sun sensor, a star sensor, a fiber optic gyroscope, an inertial navigation combination, and a high-precision accelerometer.

3. The cis-lunar space navigation satellite orbit maintenance system according to claim 1, characterized in that: The control unit includes one or more of the following control subunits, including a posture control subunit, a track control subunit, a power control subunit and a hardware drive subunit.

4. The cis-lunar space navigation satellite orbit maintenance system according to claim 1, wherein: The control unit adopts a closed-loop control method, continuously or periodically collects the status information of the satellite through the collection unit, and calculates propulsion parameters and generates control instructions in real time.

5. The cis-lunar space navigation satellite orbit maintenance system according to claim 1, characterized in that: The maximum thrust generated by the magnetoplasma propulsion module is less than 50 mN.

6. The cis-lunar space navigation satellite orbit maintenance system according to claim 5, characterized in that: The magnetic plasma propulsion module is equipped with a transformer, which realizes low-current thrust output with a current intensity of less than 10A.

7. The cis-lunar space navigation satellite orbit maintenance system according to claim 1, wherein: The execution unit further includes a power processing module, which is configured to be connected to the magnetic plasma propulsion module, receive the control instructions, and provide the power required for orbital propulsion.

8. The cis-lunar space navigation satellite orbit maintenance system according to claim 7, characterized in that: The execution unit further includes a propellant storage and supply module, which is configured to be connected to the magnetoplasma propulsion module to provide propellant.

9. The cis-lunar space navigation satellite orbit maintenance system according to claim 1, wherein: The execution unit includes at least two groups of the magnetic plasma propulsion modules, at least one of which is a backup propulsion module.

10. The cis-lunar space navigation satellite orbit maintenance system according to claim 1, wherein: The execution unit further includes a reaction flywheel module and a magnetic torquer module, and the reaction flywheel module and the magnetic torquer module are respectively connected to the control unit.

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