Spacecraft thruster failure response method

Abstract

The application provides a spacecraft thruster fault response method, comprising: transferring a small geostationary orbit satellite from an earth transfer orbit to a geostationary orbit through three stages; the small geostationary orbit satellite comprises an orbit transfer chemical thruster, an attitude control chemical thruster and an electric thruster, wherein, in the second stage of the transfer of the small geostationary orbit satellite, a fault response scheme is started according to a fault response strategy of "first electric propulsion, then orbit transfer chemical thruster, and then attitude control chemical thruster", and the fault response scheme comprises: when the electric thruster is faulty, the orbit transfer chemical thruster is started; when both the electric thruster and the orbit transfer chemical thruster are faulty, the attitude control chemical thruster is started.

Description

TECHNICAL FIELD

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

[0002] The domestic and foreign high-orbit communication satellites mainly apply chemical propulsion orbit transfer, electric propulsion station keeping, and when the chemical propulsion orbit transfer fails, the electric propulsion can be applied to complete the orbit transfer task at the cost of life span, such as the American very high frequency satellite. The domestic and foreign hybrid propulsion systems often apply the chemical propulsion system as the main force of satellite orbit transfer, and the electric propulsion system is used for on-orbit position keeping. Not only the satellite scale is huge due to the low specific impulse of the chemical propulsion, but also when the chemical propulsion system fails, although the electric propulsion system can be used to complete the orbit transfer task in a long time, the loss of satellite on-orbit life span and the failure of redundant configuration directly represent the failure of the task.

[0003] How to make the small high-orbit satellite public platform have high redundancy and reliability in orbit transfer, station keeping, and unloading is an urgent problem to be solved. SUMMARY

[0004] 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 the existing small high-orbit satellite public platform in orbit transfer, station keeping, and unloading.

[0005] To solve the above technical problems, the present application provides a spacecraft thruster fault response method, comprising:

[0006] The small geostationary orbit satellite is transferred from the earth transfer orbit to the geostationary orbit by three stages;

[0007] The small geostationary orbit satellite comprises an orbit transfer chemical thruster, an attitude control chemical thruster, and an electric thruster, wherein 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 comprises:

[0008] When the electric thruster fails, the orbit transfer chemical thruster is started;

[0009] When the electric thruster and the orbit transfer chemical thruster both fail, the attitude control chemical thruster is started.

[0010] Optionally, in the spacecraft thruster fault response method, it further comprises:

[0011] In the first stage, the orbit transfer 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;

[0012] In the second stage, the electric thruster adjusts the orbit perigee height to the second height, and the orbit inclination is adjusted to the threshold inclination and the orbit eccentricity is adjusted to the threshold eccentricity to perform orbit transfer as the control target;

[0013] In the third stage, the attitude control chemical thruster is ignited to perform point capture into the target orbit position accuracy range.

[0014] Optionally, in the spacecraft thruster failure response method,

[0015] 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;

[0016] 1 orbit transfer chemical thruster and 2 attitude control chemical thrusters form a chemical thruster group, and one chemical thruster group is arranged on the bottom plate of the +X side and the -X side respectively.

[0017] 2 electric thrusters are arranged side by side on the bottom plate of the +Y side, 2 electric thrusters are arranged side by side on the bottom plate of the -Y side, and 2 diagonally distributed electric thrusters form an electric thruster group.

[0018] Optionally, in the spacecraft thruster failure response method, in the second stage, the following is further performed:

[0019] Before the electric thruster performs orbit transfer, a first orbit determination is performed to obtain the second stage initial orbit precise orbit element, the satellite total mass, and the mass center, and the electric thruster state is set according to the first orbit determination result;

[0020] After the control target of the second stage is achieved, the electric thruster is turned off;

[0021] 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-seeking mode to the earth-keeping mode when the electric thruster is ignited;

[0022] 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-seeking mode when the electric thruster is ignited, and the electric thruster is automatically turned on to perform orbit transfer.

[0023] Optionally, in the spacecraft thruster failure response method, in the second stage, step one is included:

[0024] If one or two electric thrusters in a group of electric thrusters fail, the group of electric thrusters is in failure;

[0025] First, the first electric thruster is turned on by default to perform a transfer task;

[0026] When the first electric thruster group is in failure, the second electric thruster group is switched on, and the transfer strategy is modified and uploaded according to the measured orbit to continue the transfer task;

[0027] When the first electric thruster group and the second electric thruster are both in failure, all electric thrusters are turned off, and two transfer chemical thrusters are turned on.

[0028] Optionally, in the spacecraft thruster failure response method, step one in the second stage further includes:

[0029] Before the two transfer chemical thrusters work, the ground adjusts the transfer control strategy by measuring the orbit and the characteristics of the transfer chemical thrusters, calculates the ignition time and duration of the two transfer chemical thrusters, and optimizes the controllable arc segment;

[0030] The transfer chemical thrusters are ignited in the controllable arc segment to improve the reliability of the ignition transfer and the failure handling efficiency.

[0031] Optionally, in the spacecraft thruster failure response method, in the second stage, step two includes:

[0032] When one or two transfer chemical thrusters fail, all transfer chemical thrusters are turned off, and all attitude control chemical thrusters are turned on;

[0033] The ground calculates the joint ignition time and duration of the four attitude control chemical thrusters according to the current measured orbit to ensure that the attitude control chemical thrusters are ignited in the controllable arc segment to improve the reliability of the ignition transfer and the failure handling efficiency.

[0034] Optionally, in the spacecraft thruster failure response method, in the second stage, step three includes:

[0035] When a certain attitude control chemical thruster fails, the attitude control chemical thruster and the attitude control chemical thruster arranged diagonally thereto are turned off;

[0036] The ground calculates the joint ignition time and duration of the other two attitude control chemical thrusters according to the current measured orbit, calculates the transfer control strategy, and combines the drift star to ensure that each ignition is within the controllable arc segment, and there is a relay emergency handling capability outside the domestic controllable arc segment.

[0037] Optionally, in the spacecraft thruster failure response method, in the second stage, step four is included:

[0038] When there are only two attitude control chemical thrusters, and one of the attitude control chemical thrusters fails, all attitude control chemical thrusters are turned off, the spacecraft autonomously enters a geostationary orbit and maintains a stable attitude, and the ground determines a failure strategy and software reconfiguration.

[0039] The application also provides a spacecraft thruster failure response system, comprising:

[0040] The thruster system is configured to transfer a small geostationary satellite from a transfer orbit to a geostationary orbit by three stages, wherein:

[0041] The thruster system comprises a transfer chemical thruster, an attitude control chemical thruster, and an electric thruster;

[0042] The failure mode response strategy module is configured to perform the following actions:

[0043] When the electric thruster fails, the transfer chemical thruster is turned on;

[0044] When the transfer chemical thruster fails, the electric thruster is turned on; and

[0045] When both the electric thruster and the transfer chemical thruster fail, the attitude control chemical thruster is turned on.

[0046] In the spacecraft thruster failure response method provided by the application, by turning on the transfer chemical thruster when the electric thruster fails, turning on the electric thruster when the transfer chemical thruster fails, and turning on the attitude control chemical thruster when both the electric thruster and the transfer chemical thruster fail, a failure mode response strategy for a small high-orbit satellite transfer process thruster is provided, which has the characteristics of high strategic redundancy, clear operation logic, safe and reliable implementation, etc., so that the small high-orbit satellite has high feasibility and reliability in the case of thruster failure during transfer, adapts to the mixed propulsion system design of the small high-orbit satellite public platform, and ensures the realization of the transfer task of the small high-orbit satellite in the case of thruster failure mode. BRIEF DESCRIPTION OF DRAWINGS

[0047] Figure 1 is a spacecraft thruster failure response method flowchart of an embodiment of the application;

[0048] Figure 2 is a small high-orbit satellite thruster composition and layout schematic diagram of an embodiment of the application. DETAILED DESCRIPTION

[0049] 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.

[0050] 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.

[0051] 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.

[0052] 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.

[0053] 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".

[0054] 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.

[0055] like Figure 2 As 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.

[0056] like Figure 1 , 2As 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.

[0057] 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.

[0058] 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.

[0059] 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.

[0060] 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).

[0061] 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.

[0062] The thruster failure mode mitigation strategy provided by this invention for small high-orbit satellite orbit change processes has the following advantages:

[0063] (1) It has the advantages of high strategy redundancy, clear operation logic, and safe and reliable implementation.

[0064] (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.

[0065] 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.

[0066] 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.

[0067] 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.

[0068] 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.

[0069] 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.

[0070] 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.

[0071] 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.

[0072] 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.

[0073] 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.

[0074] 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.

[0075] 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.

[0076] 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 method for handling spacecraft thruster malfunctions, characterized in that, include: The small geostationary satellite was transferred from Earth transfer orbit to geostationary orbit in three stages. The small geostationary orbit satellite includes a maneuvering chemical thruster, an attitude control chemical thruster, and an electric thruster. During the second phase of the small geostationary orbit satellite transfer, a fault response plan is activated based on the fault response strategy of "first electric propulsion, then maneuvering chemical thruster, then attitude control chemical thruster." The fault response plan includes: When the electric thruster fails, switch to another set of electric thrusters to continue the orbit change. If both sets of electric thrusters fail, activate the orbit change chemical thruster. The ground controls the orbit change strategy according to the measured orbit and calculates the ignition time and duration of the orbit change chemical thruster to optimize the measurable arc segment. When both the electric thruster and the orbit-changing chemical thruster fail, all attitude control chemical thrusters are activated. The ground calculates the combined ignition time and duration of the attitude control chemical thrusters based on the measured orbit to ensure that ignition is performed within the measurable arc. The electric thrusters are divided into two groups and arranged on the +Y and -Y sides of the satellite, while the orbit-changing chemical thrusters and attitude control chemical thrusters are arranged in two groups on the +X and -X sides.

2. The spacecraft thruster failure handling method as described in claim 1, characterized in that, Also includes: 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 tracking arc segment not less than the threshold tracking arc segment as the control target; In the second stage, while the electric thruster adjusts to the second altitude at the perigee of the track, the track inclination is adjusted to the threshold inclination and the track eccentricity is adjusted to the threshold eccentricity as the control target to perform the track change; In the third stage, the attitude control chemical thruster ignites to perform fixed-point capture of the target by entering the target orbital accuracy range.

3. The spacecraft thruster failure handling method as described in claim 2, characterized in that, A small geostationary orbit satellite includes a +X side plate, a -X side plate, a +Y side plate, a -Y side plate, and a base plate that form the accommodating space; One orbital-changing chemical thruster and two attitude control chemical thrusters form a chemical thruster group, with one chemical thruster group arranged on the outer surface of the bottom plate compartment on the +X side and the -X side respectively. Two electric thrusters are arranged side by side on the outer surface of the bottom compartment on the +Y side, and two electric thrusters are arranged side by side on the outer surface of the bottom compartment on the -Y side. The two diagonally distributed electric thrusters form a group of electric thrusters.

4. The spacecraft thruster failure handling method as described in claim 3, characterized in that, The following also applies during the second phase: Before the electric thruster performs the orbit change, a first orbit determination is performed to obtain the initial orbital precision elements, total satellite mass, and center of mass for the second stage. The electric thruster state is then set based on the results of the first orbit determination. Once the control objective of the second stage is achieved, the electric thruster is shut down. 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 sun-oriented mode when the electric thruster is ignited to the Earth-keeping mode. 1.5 hours after the electric thruster enters perigee, the small geostationary satellite automatically switches from Earth-keeping mode to the orbit-changing Sun-aligning mode when the electric thruster is ignited, and the electric thruster automatically starts and ignites to change orbit.

5. The spacecraft thruster failure handling method as described in claim 4, characterized in that, The second phase includes, step one: If one or two electric thrusters in a group of electric thrusters fail, then the group of electric thrusters is faulty. The first electric thruster is activated by default to perform the orbital change mission. 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.

6. The spacecraft thruster failure handling method as described in claim 5, characterized in that, Step one in the second phase also 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.

7. The spacecraft thruster failure handling method as described in claim 6, characterized in that, The second phase 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.

8. The spacecraft thruster failure handling method as described in claim 7, characterized in that, The second phase 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.

9. The spacecraft thruster failure handling method as described in claim 8, characterized in that, The second phase 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.

10. A spacecraft thruster failure response system, characterized in that, include: 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, switch to another set of electric thrusters to continue the orbit change. If both sets of electric thrusters fail, activate the orbit change chemical thruster. The ground controls the orbit change strategy according to the measured orbit and calculates the ignition time and duration of the orbit change chemical thruster to optimize the measurable arc segment. When both the electric thruster and the orbit-changing chemical thruster fail, all attitude control chemical thrusters are activated. The ground calculates the combined ignition time and duration of the attitude control chemical thrusters based on the measured orbit to ensure that ignition is performed within the measurable arc. The electric thrusters are divided into two groups and arranged on the +Y and -Y sides of the satellite, while the orbit-changing chemical thrusters and attitude control chemical thrusters are arranged in two groups on the +X and -X sides.

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