Small geostationary orbit satellite

Abstract

The invention discloses a small geostationary orbit satellite which comprises two groups of electric thrusters, two orbit transfer chemical thrusters, two groups of attitude control chemical thrusters and a fault mode coping strategy module, and each group of electric thrusters comprises two electric thrusters arranged on a diagonal line. The electric thrusters are arranged on the outer side surfaces of bottom plate cabins on the + Y side and the-Y side of the main load-bearing structure of the platform bin, the priorities of the two electric thruster sets are different, and the two orbital transfer chemical thrusters are arranged on the outer side surfaces of the bottom plate cabins on the + X side and the-X side of the main load-bearing structure of the platform bin correspondingly. Each attitude control chemical thruster set comprises two attitude control chemical thrusters arranged on the diagonal line, the attitude control chemical thrusters are arranged on the two sides of the orbital transfer chemical thrusters, the fault mode coping strategy module controls all the thrusters according to the priority sequence, and the ground updates an orbital transfer control strategy based on the adopted thruster types. The satellite orbital transfer process is high in strategy redundancy, clear in operation logic and safe and reliable in implementation.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aerospace technology, in particular to a spacecraft thruster fault response method.

[0002] The present application is a divisional application of the parent application entitled "Spacecraft thruster fault response method" (application number: 2022107881974, filing date: July 6, 2022). BACKGROUND

[0003] Domestic and foreign high-orbit communication satellites mainly use chemical propulsion for orbit transfer and electric propulsion for position maintenance. When the chemical propulsion for orbit transfer fails, the electric propulsion can be used to complete the orbit transfer task at the cost of life, such as the American Extremely High Frequency Satellite. Domestic and foreign hybrid propulsion systems often use chemical propulsion systems as the main force for satellite orbit transfer, and electric propulsion systems for on-orbit position maintenance. Not only does the low specific impulse of chemical propulsion make the satellite large in size, but also when the chemical propulsion system fails, although it is possible to use the electric propulsion system to complete the orbit transfer task in a long time, the loss of satellite on-orbit life and the failure of redundant configuration directly represent the failure of the mission.

[0004] How to make small high-orbit satellite public platforms have extremely high redundancy and reliability in orbit transfer, position maintenance, and unloading is a problem that needs to be solved urgently. SUMMARY

[0005] The purpose of the present application is to provide a spacecraft thruster fault response method to solve the problem of low redundancy and reliability of existing small high-orbit satellite public platforms in orbit transfer, position maintenance, and unloading.

[0006] To solve the above technical problems, the present application provides a spacecraft thruster fault response method, comprising: The small geostationary orbit satellite is transferred from the Earth transfer orbit to the geostationary orbit by three stages; The small geostationary orbit satellite includes an orbit transfer chemical thruster, an attitude control chemical thruster, and an electric thruster. In the second stage of the transfer of the small geostationary orbit satellite, a fault response scheme is started according to the fault response strategy of "first electric propulsion, then orbit transfer chemical thruster, and then attitude control chemical thruster", and the fault response scheme includes: When the electric thruster fails, the orbit transfer chemical thruster is turned on; When the electric thruster and the orbit transfer chemical thruster both fail, the attitude control chemical thruster is turned on.

[0007] Optionally, in the spacecraft thruster fault response method, it further comprises: In the first stage, the orbit chemical thruster is ignited to quickly raise the orbit perigee height to above the first height, and the domestic TT&C arc segment is not less than the threshold TT&C arc segment to perform orbit transfer as the control target; In the second stage, the electric thruster adjusts the orbit perigee height to the second height, the orbit inclination to the threshold inclination, and the orbit eccentricity to the threshold eccentricity as the control target to perform orbit transfer; In the third stage, the attitude control chemical thruster is ignited to perform point capture into the target orbit position accuracy range.

[0008] Optionally, in the spacecraft thruster failure response method, The small geostationary satellite includes a +X side plate, an -X side plate, a +Y side plate, an -Y side plate, and a bottom plate forming a containing space; 1 orbit chemical thruster and 2 attitude control chemical thrusters form a chemical thruster group, which is arranged on the outer surface of the bottom plate on the +X side and the -X side, respectively; 2 electric thrusters are arranged side by side on the outer surface of the bottom plate on the +Y side, and 2 electric thrusters are arranged side by side on the outer surface of the bottom plate on the -Y side, and the 2 diagonally distributed electric thrusters form an electric thruster group.

[0009] Optionally, in the spacecraft thruster failure response method, in the second stage, the following is further performed: Before the electric thruster performs orbit transfer, a first orbit determination is performed to obtain the second stage initial orbit precise orbit elements, the total mass of the satellite, and the center of mass, and the electric thruster state is set according to the results of the first orbit determination; After the control target of the second stage is achieved, the electric thruster is turned off; When the electric thruster enters the perigee 1.5 hours before, the electric thruster is automatically turned off, and the small geostationary satellite is automatically converted from the orbit transfer sun-keeping mode to the earth-keeping mode when the electric thruster is ignited; When the electric thruster enters the perigee 1.5 hours after, the small geostationary satellite is automatically converted from the earth-keeping mode to the orbit transfer sun-keeping mode when the electric thruster is ignited, and the electric thruster is automatically turned on to perform orbit transfer.

[0010] Optionally, in the spacecraft thruster failure response method, in the second stage, step one is included: If one or two electric thrusters in an electric thruster group fail, the electric thruster group is faulty; First, the first electric thruster is turned on by default to perform orbit transfer tasks; When the first electric thruster group malfunctions, the second electric thruster group is switched to ignition, and the orbit change strategy is modified and applied according to the measured orbit to continue the orbit change mission. When both the first and second electric thrusters malfunction, all electric thrusters are shut down, and the two variable-orbit chemical thrusters are activated simultaneously.

[0011] Optionally, in the aforementioned spacecraft thruster failure response method, step one in the second stage further includes: Before the two maneuvering chemical thrusters were put into operation, the ground controlled the maneuvering strategy by measuring the orbit and the characteristics of chemical propulsion maneuvering, and calculated the ignition time and duration of the two maneuvering chemical thrusters in order to optimize the measurable arc segment. In the measurable arc segment, the orbit is measured, calculated, injected, and the chemical thruster for orbit change is ignited to improve the reliability of orbit change and the efficiency of fault handling.

[0012] Optionally, in the aforementioned spacecraft thruster failure response method, the second stage includes step two: When one or two orbital maneuvering chemical thrusters fail, shut down all orbital maneuvering chemical thrusters and activate all attitude control chemical thrusters. The ground system calculates the timing and duration of the combined ignition of the four attitude control chemical thrusters based on the current track measurement trajectory. This ensures that the track measurement, calculation, injection, and ignition of the attitude control chemical thrusters are carried out within the measurable arc segment, thereby improving the reliability of ignition track changes and the efficiency of fault handling.

[0013] Optionally, in the aforementioned spacecraft thruster failure response method, the second stage includes step three: When a certain attitude control chemical thruster fails, shut down that attitude control chemical thruster and the attitude control chemical thrusters located diagonally opposite it. Based on the current orbit determination, the ground calculates the timing and duration of the joint ignition of the other two attitude control chemical thrusters, calculates the orbit change control strategy, and combines it with satellite drift to ensure that each ignition is within the measurable arc segment, and that there is a relay emergency handling capability outside the domestic measurable arc segment.

[0014] Optionally, in the aforementioned spacecraft thruster failure response method, the second stage includes step four: When there are only two attitude control chemical thrusters, and one of them fails, all attitude control chemical thrusters are shut down, the satellite autonomously enters a stable attitude maintenance mode towards Earth, and the ground assesses the fault and implements strategies and software reconfiguration.

[0015] The present invention also provides a spacecraft thruster failure response system, comprising: The thrust system is configured to transfer small geostationary satellites from Earth transfer orbit to geostationary orbit in three stages, wherein: The thrust system includes a variable-orbit chemical thruster, an attitude control chemical thruster, and an electric thruster; The fault mode response strategy module is configured to perform the following actions: When the electric thruster fails, activate the orbital-changing chemical thruster. When the chemical thruster fails, the electric thruster is activated; and When both the electric thruster and the orbital change chemical thruster fail, activate the attitude control chemical thruster.

[0016] The spacecraft thruster failure handling method provided by this invention provides a thruster failure mode handling strategy for small high-orbit satellites during orbit change by activating the orbit-changing chemical thruster when the electric thruster fails, activating the electric thruster when the orbit-changing chemical thruster fails, and activating the attitude control chemical thruster when both the electric thruster and the orbit-changing chemical thruster fail. This strategy features high redundancy, clear operational logic, and safe and reliable implementation, making it highly feasible and reliable for small high-orbit satellites in the event of thruster failure during orbit change. It is suitable for the hybrid propulsion system design of small high-orbit satellites using a shared platform, ensuring the continued orbit change mission under thruster failure mode. Attached Figure Description

[0017] Figure 1 This is a schematic flowchart of a spacecraft thruster failure handling method according to an embodiment of the present invention; Figure 2 This is a schematic diagram of the composition and layout of a small high-orbit satellite thruster according to an embodiment of the present invention. Detailed Implementation

[0018] The spacecraft thruster failure handling method proposed in this invention will be further described in detail below with reference to the accompanying drawings and specific embodiments. The advantages and features of this invention will become clearer from the following description and claims. It should be noted that the drawings are all in a very simplified form and use non-precise scales, and are only used to facilitate and clarify the illustration of the embodiments of this invention.

[0019] Furthermore, unless otherwise stated, features in different embodiments of the present invention can be combined with each other. For example, a feature in the second embodiment can replace a corresponding or functionally identical or similar feature in the first embodiment, and the resulting embodiment will also fall within the scope of disclosure or description of this application.

[0020] The core idea of ​​this invention is to provide a method for dealing with spacecraft thruster failures, so as to solve the problems of low redundancy and reliability of existing small high-orbit satellite common platforms in orbit change, position maintenance, and unloading.

[0021] To achieve the above-mentioned ideas, the present invention provides a method for handling spacecraft thruster failures, comprising: a thrust system configured to transfer a small geostationary satellite from a Earth transfer orbit to a geostationary orbit in three stages, wherein: the thrust system includes a maneuvering chemical thruster, an attitude control chemical thruster, and an electric thruster; and a failure mode response strategy module configured to perform the following actions: when the electric thruster fails, activate the maneuvering chemical thruster; when the maneuvering chemical thruster fails, activate the electric thruster; and when both the electric thruster and the maneuvering chemical thruster fail, activate the attitude control chemical thruster.

[0022] This invention discloses a strategy for handling thruster failure modes during the orbit change process of small high-orbit satellites, such as... Figure 1 As shown, it utilizes the design of electric thrusters, orbit-changing chemical thrusters, and attitude control chemical thrusters as backups for each other when a small high-orbit satellite changes orbit. In the event of a failure of any thruster, a fault response plan is activated according to the fault response strategy of "first electric propulsion, then orbit-changing chemical thruster, then attitude control chemical thruster".

[0023] This invention discloses a strategy for handling thruster failure modes during the orbit change process of small high-orbit satellites. This strategy includes transferring the small geostationary orbit satellite from a transfer orbit to a geostationary orbit in three stages: In the first stage, the orbit change chemical thruster ignites to rapidly increase the perigee altitude to above a first altitude, with the domestic tracking arc segment not less than a threshold tracking arc segment as the control target for orbit change; in the second stage, the electric thruster adjusts the perigee altitude to a second altitude, while simultaneously adjusting the orbit inclination and eccentricity to a threshold inclination and threshold eccentricity as the control targets for orbit change; in the third stage, the attitude control chemical thruster ignites to perform stationary capture with the goal of entering the target orbital position accuracy range. This approach, primarily using electric propulsion for orbit change and supplemented by a layered, two-stage backup chemical propulsion system, is a first both domestically and internationally. It provides the small high-orbit satellite common platform with extremely high redundancy and reliability in orbit change, position maintenance, and unloading, adapting to the hybrid propulsion system design of the small high-orbit satellite common platform. This solves the problem of balancing flexible configuration, high cost-effectiveness, and high reliability for the small high-orbit satellite common platform.

[0024] like Figure 2As shown, the small geostationary orbit satellite includes a platform module main load-bearing structure configured to provide accommodating space, wherein the platform module main load-bearing structure includes a satellite-rocket connection ring; multiple tanks arranged in the accommodating space and directly mounted on the satellite-rocket connection ring; and gas path components arranged in the accommodating space such that the load of the gas path components is transferred to the satellite-rocket connection ring through the platform module main load-bearing structure. The platform compartment's main load-bearing structure also includes a main load-bearing truss assembly, +X side plates, -X side plates, +Y side plates, -Y side plates, and a base plate, wherein: the +X side plates, -X side plates, +Y side plates, -Y side plates, and the base plate constitute the accommodating space; the main load-bearing truss assembly is located within the accommodating space and divides the accommodating space into multiple areas; the main load-bearing truss assembly supports the +X side plates, -X side plates, +Y side plates, -Y side plates, and the base plate, and transfers the loads of the +X side plates, -X side plates, +Y side plates, and -Y side plates to the base plate; the axes of the storage tank and the gas path assembly are both perpendicular to the base plate. The star-rocket connecting ring is integrally formed with the base plate, the inner portion of the star-rocket connecting ring is flush with the inner surface of the base plate, and the outer portion of the star-rocket connecting ring protrudes from the outer surface of the base plate and is connected to the carrier. One set of orbit-changing chemical thrusters and two sets of attitude control chemical thrusters form a group, with one group arranged on the outer surface of the bottom deck on the +X and -X sides respectively; two sets of electric thrusters are arranged side by side to form a group, with one group arranged on the outer surface of the bottom deck on the +Y and -Y sides respectively.

[0025] like Figure 1 , 2 As shown, the thruster failure mode response strategy provided by this invention for the small high-orbit satellite orbit change process uses a 300mN electric thruster as the default mode for the orbit change mission. The two electric thrusters arranged diagonally form a group for the orbit change mission, and the two groups of electric thrusters serve as backups for each other. When electric thruster 1 (1) or electric thruster 3 (3) fails, the combination of electric thruster 2 (2) and electric thruster 4 (4) is switched, and the orbit change strategy is modified and added according to the orbit determination, and the orbit change mission continues to be implemented. When electric thruster 2 (2) or electric thruster 4 (4) fails, the electric thruster is turned off, and the orbit change chemical thruster 1 (5) and orbit change chemical thruster 2 (6) are turned on. The orbit change chemical thrusters are all selected from the same batch of 150N bicomponent chemical thrusters.

[0026] The fault mode response strategy for thrusters during the orbit change process of small high-orbit satellites provided by this invention involves adjusting the orbit change control strategy on the ground by determining the orbit and the characteristics of chemical propulsion before the operation of orbit change chemical thrusters 1 (5) and 2 (6), designing the ignition time and duration to optimize the measurable arc segment, determining the orbit, calculating, injecting and implementing the orbit change chemical thruster ignition during the measurable arc segment, thereby improving the reliability of ignition and orbit change and the efficiency of fault handling.

[0027] The fault mode response strategy for thrusters during the orbit change process of small high-orbit satellites provided by this invention is as follows: when the orbit change chemical thruster 1 (5) or the orbit change chemical thruster 2 (6) fails, the two orbit change chemical thrusters are shut down and all attitude control chemical thrusters are turned on. The ground calculates the time and duration of joint ignition of the four 10N attitude control chemical thrusters based on the current orbit measurement, so as to ensure that the orbit measurement, calculation, injection and implementation of orbit change chemical thruster ignition are carried out as much as possible in the measurement and control arc segment, thereby improving the reliability of ignition and orbit change and the efficiency of fault handling.

[0028] The fault response strategy for thrusters during the orbit change process of small high-orbit satellites provided by this invention is as follows: when attitude control chemical thruster 1 (7) or attitude control chemical thruster 4 (10) fails, attitude control chemical thruster 1 (7) and attitude control chemical thruster 4 (10) are shut down. The ground calculates the time and duration of joint ignition of the two attitude control chemical thrusters based on the current orbit measurement, designs an orbit change control strategy, and combines the drifting satellite to ensure that each ignition is within the measurement and control arc and that there is a relay emergency handling capability outside the domestic measurement and control arc.

[0029] The fault response strategy for the thruster during the orbit change process of the small high-orbit satellite provided by this invention is as follows: when the attitude control chemical thruster 2 (8) or attitude control chemical thruster 3 (9) fails, the attitude control chemical thruster 2 (8) or attitude control chemical thruster 3 (9) is turned off, the satellite autonomously enters the stable attitude maintenance on the ground, and the ground judges the fault implementation strategy (including software reconfiguration).

[0030] The priorities and positions of electric thrusters 1 and 3, and 2 and 4, can be interchanged, with equal priority. The above steps are based on the "electric propulsion orbit change process," and are designed with the electric thrusters, orbit change chemical thrusters, and attitude control chemical thrusters as backups for each other. When a fault occurs (in this case, it should be an electric thruster failure, as electric propulsion is used for orbit change), the fault response strategy is activated according to the sequence "electric propulsion first, then orbit change chemical thruster, then attitude control chemical thruster." That is, if the electric thruster fails, a solution is first sought within the redundant electric thrusters; if the electric thruster cannot resolve the issue, the chemical orbit change thruster is activated first. The chemical orbit change thruster has a large thrust (150N) and high orbit change efficiency, making it the primary backup for electric propulsion orbit change. If both the electric thruster and the chemical orbit change thruster fail, only the chemical attitude thruster can be activated as a last resort, with lower orbit change efficiency and a longer time required to achieve the orbit change objective. Therefore, this invention has high strategy redundancy, clear operational logic, and is safe and reliable to implement. If the chemical thruster fails in the first stage, the electric thruster will be used as a backup.

[0031] The thruster failure mode response strategy provided by this invention for the orbit change process of small high-orbit satellites has the following advantages: (1) It has the advantages of high strategy redundancy, clear operation logic, and safe and reliable implementation.

[0032] (2) It enables small high-orbit satellites to have extremely high feasibility and reliability in the event of thrust failure during orbit change, adapts to the hybrid propulsion system design of the common platform of small high-orbit satellites, and ensures the realization of the orbit change mission under the thrust failure mode of small high-orbit satellites.

[0033] In one embodiment of the present invention, in the orbit transfer method for a small geostationary satellite, the first altitude is 8000 km, the second altitude is 35786 km, the threshold measurement and control arc is 3 hours, the threshold inclination is 0 degrees, and the threshold eccentricity is 0 degrees.

[0034] In one embodiment of the present invention, during the first stage, the following is also performed: the orbit-changing chemical thruster raises the perigee altitude of the small geostationary satellite to above a first altitude within 120 hours; after the perigee altitude of the small geostationary satellite is raised to the first altitude, the orbit-changing chemical thruster is shut down.

[0035] In one embodiment of the present invention, the second stage further includes: performing a first orbit determination before the electric thruster performs the orbit change to obtain the initial orbital precision elements, total satellite mass and centroid of the second stage; setting the electric thruster state based on the results of the first orbit determination; and shutting down the electric thruster after the control objective of the second stage is achieved.

[0036] In one embodiment of the present invention, the second stage further includes: 1.5 hours before the electric thruster enters perigee, the electric thruster automatically shuts down, and the small geostationary satellite automatically switches from the orbit-changing and sun-aligning mode when the electric thruster ignites to the Earth-keeping mode; 1.5 hours after the electric thruster enters perigee, the small geostationary satellite automatically switches from the Earth-keeping mode to the orbit-changing and sun-aligning mode when the electric thruster ignites, and the electric thruster automatically starts up and ignites for orbit changing.

[0037] In one embodiment of the present invention, the third stage further includes: before the attitude control chemical thruster is ignited, a second orbit determination is performed to obtain the initial orbital precision elements, total satellite mass, and centroid of the third stage; the attitude control chemical thruster state is set according to the results of the second orbit determination; after entering the target orbital accuracy range, the attitude control chemical thruster is shut down and the working propellant flow of the orbit-changing chemical thruster is cut off to ensure the safety of the propulsion system after positioning.

[0038] In one embodiment of the present invention, the method further includes: when the orbit-changing chemical thruster fails, the attitude control chemical thruster and / or the electric thruster serve as backups; when the electric thruster fails, the attitude control chemical thruster and / or the orbit-changing chemical thruster serve as backups; when the attitude control chemical thruster fails, the orbit-changing chemical thruster and / or the electric thruster serve as backups.

[0039] In one embodiment of the present invention, the small geostationary orbit satellite has a launch mass of 2300 kg and is launched into a super geosynchronous orbit. The apogee altitude of the super geosynchronous orbit is 48000 km, and the inclination of the super geosynchronous orbit is 28.5 degrees. The launch point of the small geostationary orbit satellite is 101 degrees east longitude ± 0.05 degrees.

[0040] In one embodiment of the present invention, the rated thrust of the orbit-changing chemical thruster is 150N, and there are 2 units; the rated thrust of the electric thruster is 300mN, and there are 4 units, with 2 electric thrusters arranged side by side to form a group of electric thrusters, and the two groups of electric thrusters are distributed diagonally; the rated thrust of the attitude control chemical thruster is 10N, and there are 4 units, with 1 orbit-changing chemical thruster and 2 attitude control chemical thrusters forming a group of chemical thrusters, and the two groups of chemical thrusters are distributed diagonally.

[0041] This embodiment also provides a spacecraft thruster failure response system, including: a thrust system configured to transfer a small geostationary satellite from a Earth transfer orbit to a geostationary orbit in three stages, wherein: the thrust system includes a maneuvering chemical thruster, an attitude control chemical thruster, and an electric thruster; and a failure mode response strategy module configured to perform the following actions: when the electric thruster fails, activate the maneuvering chemical thruster; when the maneuvering chemical thruster fails, activate the electric thruster; and when both the electric thruster and the maneuvering chemical thruster fail, activate the attitude control chemical thruster.

[0042] In summary, the above embodiments have provided detailed descriptions of different configurations for handling spacecraft thruster malfunctions. Of course, this invention includes, but is not limited to, the configurations listed in the above embodiments. Any modifications made based on the configurations provided in the above embodiments are within the scope of protection of this invention. Those skilled in the art can apply the principles outlined in the above embodiments to other similar applications.

[0043] The various embodiments in this specification are described in a progressive manner, with each embodiment focusing on its differences from other embodiments. Similar or identical parts between embodiments can be referred to interchangeably. For the systems disclosed in the embodiments, since they correspond to the methods disclosed in the embodiments, the descriptions are relatively simple; relevant parts can be referred to the method section.

[0044] The above description is merely a description of preferred embodiments of the present invention and is not intended to limit the scope of the present invention in any way. Any changes or modifications made by those skilled in the art based on the above disclosure shall fall within the protection scope of the claims.

Claims

1. A small geostationary orbit satellite, characterized in that, include: Two sets of electric thrusters, each set including two electric thrusters arranged diagonally, the electric thrusters being arranged on the outer surface of the bottom plate of the main load-bearing structure of the platform module of the small geostationary satellite on the +Y and -Y sides, the two sets of electric thrusters having different priorities; Two orbit-changing chemical thrusters are respectively installed on the outer surface of the bottom plate of the main load-bearing structure of the platform compartment of the small geostationary orbit satellite on the +X side and the -X side. Two sets of attitude control chemical thruster groups, each set comprising two attitude control chemical thrusters arranged diagonally, the attitude control chemical thrusters being positioned on either side of the orbital change chemical thruster; and The fault mode response strategy module is configured to control the electric thruster group, the orbit-changing chemical thruster, and the attitude control chemical thruster group to implement fault response. When the higher-priority electric thruster group fails, the system switches to the other electric thruster group. If both electric thruster groups fail, the two orbit-changing chemical thrusters are activated, and the ground adjusts the orbit-changing control strategy according to the orbit determination, calculating the ignition timing and duration of the orbit-changing chemical thrusters to optimize the measurable arc. If at least one orbit-changing chemical thruster fails, the two groups of... The attitude control chemical thruster group: the ground calculates the joint ignition time and duration of the attitude control chemical thrusters based on the measurement orbit. If at least one attitude control chemical thruster in any group fails, the attitude control chemical thruster and its group of attitude control chemical thrusters are shut down. The ground calculates the joint ignition time and duration of another attitude control chemical thruster group based on the current measurement orbit. If at least one attitude control chemical thruster in the other group fails, all attitude control chemical thrusters are shut down. The satellite autonomously enters a stable attitude maintenance state towards the ground, and the ground assesses the fault and implements a strategy.

2. The small geostationary orbit satellite as described in claim 1, characterized in that, The failure mode response strategy module is also configured to control the electric thruster group, the orbit-changing chemical thruster, and the attitude control chemical thruster group to transfer the small geostationary satellite from the Earth transfer orbit to the geostationary orbit in three stages.

3. The small geostationary orbit satellite as described in claim 2, characterized in that, The three stages include: In the first stage, the orbit change chemical thruster is ignited to rapidly raise the orbital perigee altitude to above the first altitude, and the orbit change is executed with the domestic telemetry and control arc segment not less than the threshold telemetry and control arc segment as the control target; In the second stage, while controlling the electric thruster to adjust to a second altitude at the orbital perigee height, the orbital inclination is adjusted to a threshold inclination angle, and the orbital eccentricity is adjusted to a threshold eccentricity as the control target to perform orbital change; and In the third stage, the attitude control chemical thruster is ignited to perform fixed-point capture of the target by entering the target orbital accuracy range.

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