Method for analyzing the effect of a space thruster plume on the mechanics of a satellite sail

Abstract

The application provides a method for analyzing the influence of plume of a space thruster on the satellite sailboard mechanics, comprising the following steps: S1, determining a plume influence characteristic angle according to the specific installation positions of the thruster and the sailboard on the satellite; S2, analyzing the plume acting force on the affected area of the sailboard; S3, plume mechanics simulation analysis of the thruster; S4, momentum impact force analysis; S5, calculating the resultant force of the plume impact force; S6, combining the working mode of the thruster to analyze the angular momentum; the method can quickly calculate the interference torque and angular momentum of the plume of the thruster on the satellite. The method can analyze and evaluate the influence of the plume of the thruster on the satellite sailboard mechanics when the satellite configuration layout is designed, and can provide a reference for the satellite configuration layout and the configuration of the attitude and orbit control products, so as to shorten the design cycle and improve the design efficiency.

Description

Technical Field

[0001] This invention belongs to the field of spacecraft mechanical influence analysis, specifically, it relates to an analysis method for the mechanical influence of space thruster plumes on satellite solar panels. Background Technology

[0002] A plume is a high-speed, high-temperature gas stream ejected by a space thruster during operation. It is characterized by high gas molecule concentration, electron density, and electron collision frequency, and is a weak plasma containing unburned propellant, ionized gas, and solid particles. In a vacuum, the plume rapidly expands and diffuses, forming complex flow field structures, including shock waves, expansion waves, and recirculation regions. The effects of a plume on spacecraft mainly include electromagnetic interference caused by its plasma characteristics, degradation of instrument performance due to deposition on spacecraft surfaces, thermal effects caused by heating sensitive components, and unexpected force or torque interference generated by impacting spacecraft surfaces.

[0003] In the aerospace field, to avoid or eliminate the mechanical impact of thruster plumes on spacecraft, the common practice is to use empirical values ​​of the thruster plume's semi-cone angle to allow sufficient space margin in the configuration and layout design to ensure that the spacecraft body is not within the plume's impact range. However, when space constraints cause the spacecraft body or solar panels to be at a critical distance from the thruster plume or to directly enter the plume, it is necessary to combine numerical analysis results of the plume field with mechanical coupling analysis, or conduct ground-based tests for verification. The disadvantages of this method are its long analysis cycle and high cost.

[0004] Currently, the relevant existing technologies include: A method for determining the thermal and kinetic effects of a 10N thruster plume (patent document CN102169047B) discloses a method for determining the thermal and kinetic effects of a 10N thruster plume. This method establishes the satellite's geometric dimensions and coordinate system, divides the solar array and communication antenna into grids, calculates the plume's interference force and heat flux distribution, uses fitting functions F(r, κ, β) and H(r, κ, β) to describe the plume field effects, and performs numerical interpolation and analytical expression to simplify the calculation process. However, the overall calculation steps are still relatively complex and computationally intensive. Summary of the Invention

[0005] In view of the deficiencies in the prior art, the purpose of this invention is to provide an analytical method for the influence of space thruster plumes on the mechanical properties of satellite solar panels.

[0006] The method for analyzing the impact of space thruster plumes on satellite solar panels according to the present invention includes: Step S1: Determine the characteristic angle of plume influence based on the specific installation positions of the thruster and solar panels on the satellite; Step S2: Analyze the plume forces acting on the affected area of ​​the windsurfing system; Step S3: Thrust plume dynamics simulation analysis; Step S4: Momentum impact force analysis; Step S5: Calculate the resultant force of the plume impact; Step S6: Perform angular momentum analysis based on the thruster's operating mode.

[0007] Preferably, in step S1: the semi-cone angle α at which the plume begins to enter the sail is determined based on the specific installation positions of the thruster and the sail on the satellite, and β is the known plume influence envelope semi-cone angle.

[0008] Preferably, in step S2: the plume force acting on the affected area of ​​the sail can be divided into two components F in the Y and Z directions. Y F Z Each directional component of the force can be decomposed into a feather momentum impact force F. Y动量 F Z动量 and local static pressure F Y压力 F Z压力 : F Y = F Y动量 +F Y压力 F Z = F Z动量 +F Z压力。

[0009] Preferably, in step S3: the mass flow rate field and pressure field of the thruster plume are simulated and analyzed using the fluid analysis software Fluent, and the mass flow rate field is integrated along the circumference to obtain the curve of the mass flow rate percentage as a function of the plume half-cone angle. This curve yields the mass flow rate percentage δ within the plume annulus from half-cone angle α to β, which is the ratio of the plume momentum impact force to the thruster's rated thrust F. T The ratio.

[0010] Preferably, in step S4: based on the size of the affected area on the axial cross-section of the plume field, the corresponding plume center angles θ in the Y and Z directions are obtained. y θ z Thus, a momentum impact force can be obtained: F Y动量 =F T ×δ×θ y / 360 F Z动量 =F T ×δ×θ Z / 360 Preferably, in step S5: the static pressure is obtained based on the plume pressure field and the area of ​​the area of ​​the sail affected by the plume in the corresponding direction. F Y压力 =P L ×A Y F Z压力 =P L ×A Z Among them, P L For the local static pressure, A Y A Z The area affected in the corresponding direction; Preferably, step S6 includes: Step S6.1: Calculate the resultant force of the plume impact: F Y = F Y动量 +F Y压力 F Z = F Z动量 +F Z压力 Step S6.2: Calculate the torque of the plume force on the three coordinate axes of the satellite's center of mass based on the distance of the affected area from the satellite's center of mass; Step S6.3: By combining the working mode of the thruster, the corresponding angular momentum can be obtained.

[0011] The analysis system for the influence of space thruster plumes on satellite solar panels according to the present invention includes: Module M1: Determine the characteristic angle of plume influence based on the specific installation positions of the thruster and solar panels on the satellite; Module M2: Analyzes the plume forces acting on the affected area of ​​the windsurfing system; Module M3: Simulation and analysis of thruster plume dynamics; Module M4: Momentum Impact Force Analysis; Module M5: Calculates the resultant force of the plume impact; Module M6: Performs angular momentum analysis based on the thruster's operating mode.

[0012] Preferably, in module M1: the semi-cone angle α at which the plume begins to enter the solar panel is determined based on the specific installation positions of the thruster and solar panel on the satellite, and β is the known plume influence envelope semi-cone angle; In module M2: the plume force acting on the affected area of ​​the windsurfing can be divided into two components F in the Y and Z directions. Y F Z Each directional component of the force can be decomposed into a feather momentum impact force F. Y动量 F Z动量 and local static pressure FY压力 F Z压力 : F Y = F Y动量 +F Y压力 F Z = F Z动量 +F Z压力 In module M3: the mass flow rate field and pressure field of the thruster plume are simulated and analyzed using the fluid analysis software Fluent. The mass flow rate field is then integrated circumferentially to obtain a curve showing the percentage of mass flow rate as a function of the plume's half-cone angle. This curve yields the mass flow rate percentage δ within the plume annulus from half-cone angle α to β, which represents the ratio of the plume's momentum impact force to the thruster's rated thrust F. T The ratio; In module M4: based on the size of the affected area on the axial cross-section of the plume field, the corresponding plume center angles θ in the Y and Z directions are obtained. y θ z Thus, a momentum impact force can be obtained: F Y动量 =F T ×δ×θ y / 360 F Z动量 =F T ×δ×θ Z / 360 In module M5: the static pressure is obtained based on the plume pressure field and the area of ​​the region on the sail affected by the plume in the corresponding direction. F Y压力 =P L ×A Y F Z压力 =P L ×A Z Among them, P L For the local static pressure, A Y A Z The area affected in the corresponding direction; The module M6 includes: Module M6.1: Calculate the resultant force of the plume impact: F Y = F Y动量 +F Y压力 F Z = F Z动量 +F Z压力 Module M6.2: Calculate the torque of the plume force on the three coordinate axes of the satellite's center of mass based on the distance of the affected area from the satellite's center of mass; Module M6.3: Combined with the thruster's operating mode, the corresponding angular momentum can be obtained.

[0013] A space thruster, characterized in that it is equipped with an analysis system for the mechanical effects of a space thruster plume on a satellite solar panel according to the present invention.

[0014] Compared with the prior art, the present invention has the following beneficial effects: 1. Based on the analysis of the specific location of the satellite solar panels affected by the space thruster plume, and combined with the numerical simulation results of the thruster plume and the working mode of the thruster, this invention can quickly calculate the interference force, interference torque and angular momentum of the thruster plume on the satellite. 2. This invention can analyze and evaluate the mechanical effects of the thruster plume on the satellite solar panels during the satellite configuration and layout design, providing a reference for satellite configuration and layout and the configuration of its attitude and orbit control products. Attached Figure Description

[0015] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings: Figure 1 This is a flowchart of the method of the present invention.

[0016] Figure 2 This is a schematic diagram showing the positions of the thruster plume and the sail of the present invention.

[0017] Figure 3 This is a curve showing the percentage of plume mass flow rate as a function of the plume half-cone angle, as presented in this invention. Detailed Implementation

[0018] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the protection scope of the present invention.

[0019] This invention provides an analytical method for the impact of space thruster plumes on satellite solar panel mechanics, which can provide a reference for satellite configuration and attitude and orbit control product setup, including: Step S1: Determine the characteristic angle of plume influence based on the specific installation positions of the thruster and solar panels on the satellite; Step S2: Analyze the plume forces acting on the affected area of ​​the windsurfing system; Step S3: Thrust plume dynamics simulation analysis; Step S4: Momentum impact force analysis; Step S5: Calculate the resultant force of the plume impact; Step S6: Perform angular momentum analysis based on the thruster's operating mode; Further, step S1 includes: determining the semi-cone angle α at which the plume begins to enter the sail based on the specific installation positions of the thruster and the sail on the satellite, where β is the known plume influence envelope semi-cone angle; Further, step S2 includes: the plume force acting on the affected area of ​​the sailboard can be divided into two components F in the Y and Z directions. Y F Z Each directional component of the force can be decomposed into a feather momentum impact force F. Y动量 F Z动量 and local static pressure F Y压力 F Z压力 : F Y = F Y动量 +F Y压力 F Z = F Z动量 +F Z压力 Further, step S3 includes: using the fluid analysis software Fluent to simulate and analyze the mass flow field and pressure field of the thruster plume, and using the circumferential integration of the mass flow field to obtain the curve of the mass flow percentage as a function of the plume half-cone angle. Through this curve, the mass flow percentage δ within the plume annulus from the half-cone angle α to β can be obtained. This value is the ratio of the plume momentum impact force to the thruster's rated thrust F. T The ratio; Further, step S4 includes: obtaining the corresponding plume center angles θ in the Y and Z directions based on the size of the affected area of ​​the sail on the axial cross-section of the plume field. y θ z Thus, a momentum impact force can be obtained: F Y动量 =F T ×δ×θ y / 360 F Z动量 =F T ×δ×θ Z / 360 Further, step S5 includes: obtaining the static pressure based on the plume pressure field and the area of ​​the region of the sail affected by the plume in the corresponding direction. F Y压力 =P L ×A Y F Z压力 =P L ×A Z Among them, P L For the local static pressure, A Y A Z The area affected in the corresponding direction; Further, step S6 includes: Step S6.1: Calculate the resultant force of the plume impact: F Y = F Y动量 +F Y压力 F Z = F Z动量 +F Z压力 Step S6.2: Calculate the torque of the plume force on the three coordinate axes of the satellite's center of mass based on the distance of the affected area from the satellite's center of mass; Step S6.3: By combining the working mode of the thruster, the corresponding angular momentum can be obtained.

[0020] Next, the present invention will be described in more detail. In a more specific embodiment, the method for analyzing the influence of the space thruster plume on the mechanical properties of the satellite solar panel includes: Step S1: Based on the specific installation positions of the 1N thruster and solar panel on the satellite, determine the semi-cone angle α at which the plume begins to enter the solar panel as 27 degrees, and β as the known thruster plume influence envelope semi-cone angle as 30 degrees. Figure 2 As shown; Step S2: The plume force on the affected part of the windsurfing can be decomposed into a force F acting on the -Y side of the windsurfing. Y (Direction towards +Y, area of ​​action is A) Y ) and the force F acting on the +Z side of the sail Z (Direction towards -Z, area of ​​action is A) Z Force F Y Heli F Z It can also be decomposed into plume flow impact force and local static pressure: F Y = F Y动量 +F Y压力 F Z = F Z动量 +F Z压力 Step S3: Calculate the mass flow rate field and pressure field of the 1N thruster plume using Fluent, and obtain the curve of mass flow rate percentage as a function of plume half-cone angle by integrating the mass flow rate field circumferentially, as shown in the figure. Figure 3As shown in the curve, the range of the half-cone angle of 25 degrees corresponds to 97% of the total mass flow, while the range outside the half-cone angle corresponds to the remaining 3% of the mass flow. The mass flow density should be less than 3% in the range of the half-cone angle of 27 to 30 degrees. In this example, considering the worst-case scenario, δ is taken as the maximum value of 3%, and the rated thrust F of the 1N thruster is... T The value is 1.45N.

[0021] Step S4: Based on the size of the affected region on the axial cross-section of the plume field, obtain the corresponding central angles θ in two directions. y θ z The angles are 2.20° and 1.18° respectively, thus yielding a momentum impact force: F Y动量 = F T ×δ×θ y / 360=1.45×0.03×2.20 / 360=2.658×10 -4 N F Z动量 = F T ×δ×θ z / 360 = 1.45 × 0.03 × 1.18 / 360 = 1.425 × 10 -4 N Step S5: Measure the area of ​​the windsurf affected by the plume, obtained through model measurement: A Y =3.291×10 -3 m 2 A Z =1.902×10 -3 m 2 Local static pressure P in the plume field L The result calculated in step S3 is taken as the worst-case scenario, with the highest value being 0.01 Pa; the static pressure is then calculated. F Y压力 =P L ×A Y =3.291×10 -3 ×0.01=3.291×10 -5 N F Z压力 =P L ×A Z =1.902×10 -3 ×0.01=1.902×10 -5 N Step S6.1: Calculate the resultant force of the plume impact: F Y = F Y动量 +F Y压力=2.987×10 -4 N F Z = F Z动量 +F Z压力 =1.615×10 -4 N Step S6.2: Based on the distance of the affected area from the satellite's center of mass, the torque of the plume force on the three coordinate axes of the satellite's center of mass can be calculated: M x =1.23×10 -5 N•m M y =3.04×10 -4 N•m M z =5.61×10 -4 N•m Step S6.3: Combining the thruster's operating mode, and assuming the thruster operates for a maximum of 120 seconds, the corresponding angular momentum can be obtained: H x =0.001 N•m•s H y =0.036 N•m•s H z =0.067 N•m•s The aforementioned torque and angular momentum are far less than the rated adjustment capability of the flywheel configured on the satellite, and the mechanical impact of the 1N thruster plume on the sail is within an acceptable range.

[0022] The present invention also provides an analysis system for the mechanical effects of space thruster plumes on satellite solar panels. The analysis system for the mechanical effects of space thruster plumes on satellite solar panels can be implemented by executing the process steps of the analysis method for the mechanical effects of space thruster plumes on satellite solar panels. That is, those skilled in the art can understand the analysis method for the mechanical effects of space thruster plumes on satellite solar panels as a preferred embodiment of the analysis system for the mechanical effects of space thruster plumes on satellite solar panels.

[0023] An analysis system for the influence of space thruster plumes on satellite solar panels, provided according to embodiments of the present invention, includes: Module M1: Determine the characteristic angle of plume influence based on the specific installation positions of the thruster and solar panels on the satellite; Module M2: Analyzes the plume forces acting on the affected area of ​​the windsurfing system; Module M3: Simulation and analysis of thruster plume dynamics; Module M4: Momentum Impact Force Analysis; Module M5: Calculates the resultant force of the plume impact; Module M6: Performs angular momentum analysis based on the thruster's operating mode; Furthermore, the module M1 includes: determining the semi-cone angle α at which the plume begins to enter the solar panel, based on the specific installation positions of the thruster and solar panel on the satellite, where β is the known plume influence envelope semi-cone angle; Furthermore, the module M2 includes: the plume force acting on the affected area of ​​the sailboard can be divided into two components F in the Y and Z directions. Y F Z Each directional component of the force can be decomposed into a feather momentum impact force F. Y动量 F Z动量 and local static pressure F Y压力 F Z压力 : F Y = F Y动量 +F Y压力 F Z = F Z动量 +F Z压力 Furthermore, module M3 includes: using the fluid analysis software Fluent to simulate and analyze the mass flow field and pressure field of the thruster plume, and using the circumferential integration of the mass flow field to obtain the curve of the mass flow percentage as a function of the plume half-cone angle. Through this curve, the mass flow percentage δ within the plume annulus from the half-cone angle α to β can be obtained. This value is the ratio of the plume momentum impact force to the thruster's rated thrust F. T The ratio; Furthermore, module M4 includes: obtaining the corresponding plume center angles θ in the Y and Z directions based on the size of the affected area of ​​the sail on the axial cross-section of the plume field. y θ z Thus, a momentum impact force can be obtained: F Y动量 =F T ×δ×θ y / 360 F Z动量 =F T ×δ×θ Z / 360 Furthermore, module M5 includes: obtaining static pressure based on the plume pressure field and the area of ​​the region of the sail affected by the plume in the corresponding direction: F Y压力 =P L ×A Y F Z压力 =P L ×A Z Among them, P L For the local static pressure, AY A Z The area affected in the corresponding direction; Furthermore, the module M6 includes: Module M6.1: Calculate the resultant force of the plume impact: F Y = F Y动量 +F Y压力 F Z = F Z动量 +F Z压力 Module M6.2: Calculate the torque of the plume force on the three coordinate axes of the satellite's center of mass based on the distance of the affected area from the satellite's center of mass; Module M6.3: Combined with the thruster's operating mode, the corresponding angular momentum can be obtained.

[0024] In summary, this invention provides a method for analyzing the mechanical impact of a space thruster plume on a satellite solar panel, comprising: Step S1: determining the plume influence characteristic angle based on the specific installation positions of the thruster and solar panel on the satellite; Step S2: analyzing the plume force acting on the affected area of ​​the solar panel; Step S3: thruster plume mechanical simulation analysis; Step S4: momentum impact force analysis; Step S5: calculating the resultant force of the plume impact; Step S6: combining the thruster's operating mode with angular momentum analysis. This method can quickly calculate the interference torque and angular momentum of the thruster plume on the satellite. This method can analyze and evaluate the mechanical impact of the thruster plume on the satellite during satellite configuration and layout design, providing a reference for satellite configuration and layout and the configuration of its attitude and orbit control products, shortening the design cycle and improving design efficiency.

[0025] Those skilled in the art will understand that, besides implementing the system and its various devices, modules, and units provided by this invention in the form of purely computer-readable program code, the same functions can be achieved entirely through logical programming of the method steps, making the system and its various devices, modules, and units of this invention function in the form of logic gates, switches, application-specific integrated circuits, programmable logic controllers, and embedded microcontrollers. Therefore, the system and its various devices, modules, and units provided by this invention can be considered as a hardware component, and the devices, modules, and units included therein for implementing various functions can also be considered as structures within the hardware component; alternatively, the devices, modules, and units for implementing various functions can be considered as both software modules implementing the method and structures within the hardware component.

[0026] In the description of this application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.

[0027] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A method for analyzing the influence of space thruster plumes on the mechanical properties of satellite solar panels, characterized in that, include: Step S1: Determine the characteristic angle of plume influence based on the specific installation positions of the thruster and solar panels on the satellite; Step S2: Analyze the plume forces acting on the affected area of ​​the windsurfing system; Step S3: Thrust plume dynamics simulation analysis; Step S4: Momentum impact force analysis; Step S5: Calculate the resultant force of the plume impact; Step S6: Perform angular momentum analysis based on the thruster's operating mode.

2. The method for analyzing the influence of space thruster plumes on satellite solar panels according to claim 1, characterized in that, In step S1: Based on the specific installation positions of the thruster and the solar panel on the satellite, the semi-cone angle α at which the plume begins to enter the solar panel is determined, and β is the known plume influence envelope semi-cone angle.

3. The method for analyzing the influence of space thruster plumes on satellite solar panels according to claim 2, characterized in that, In step S2: the plume force acting on the affected area of ​​the windsurfing can be divided into two components F in the Y and Z directions. Y F Z Each directional component of the force can be decomposed into a feather momentum impact force F. Y动量 F Z动量 and local static pressure F Y压力 F Z压力 : F Y = F Y动量 +F Y压力 F Z = F Z动量 +F Z压力。 4. The method for analyzing the influence of space thruster plumes on satellite solar panels according to claim 3, characterized in that, In step S3: the mass flow rate field and pressure field of the thruster plume are simulated and analyzed using the fluid analysis software Fluent. The mass flow rate field is then integrated circumferentially to obtain a curve showing the percentage of mass flow rate as a function of the plume's half-cone angle. This curve yields the mass flow rate percentage δ within the plume annulus from half-cone angle α to β, which represents the ratio of the plume's momentum impact force to the thruster's rated thrust F. T The ratio.

5. The method for analyzing the influence of space thruster plumes on satellite solar panels according to claim 4, characterized in that, In step S4: based on the size of the affected area on the axial cross-section of the plume field, the corresponding plume center angles θ in the Y and Z directions are obtained. y θ z Thus, a momentum impact force can be obtained: F Y动量 =F T ×δ×θ y / 360 F Z动量 =F T ×δ×θ Z / 360。 6. The method for analyzing the influence of space thruster plumes on satellite solar panels according to claim 5, characterized in that, In step S5: the static pressure is obtained based on the plume pressure field and the area of ​​the area of ​​the sail affected by the plume in the corresponding direction. F Y压力 =P L ×A Y F Z压力 =P L ×A Z Among them, P L For the local static pressure, A Y A Z The area affected in the corresponding direction.

7. The method for analyzing the influence of space thruster plumes on satellite solar panels according to claim 6, characterized in that, Step S6 includes: Step S6.1: Calculate the resultant force of the plume impact: F Y = F Y动量 +F Y压力 F Z = F Z动量 +F Z压力 Step S6.2: Calculate the torque of the plume force on the three coordinate axes of the satellite's center of mass based on the distance of the affected area from the satellite's center of mass; Step S6.3: By combining the working mode of the thruster, the corresponding angular momentum can be obtained.

8. An analysis system for the influence of space thruster plumes on the mechanical properties of satellite solar panels, comprising: Module M1: Determine the characteristic angle of plume influence based on the specific installation positions of the thruster and solar panels on the satellite; Module M2: Analyzes the plume forces acting on the affected area of ​​the windsurfing system; Module M3: Simulation and analysis of thruster plume dynamics; Module M4: Momentum Impact Force Analysis; Module M5: Calculates the resultant force of the plume impact; Module M6: Performs angular momentum analysis based on the thruster's operating mode.

9. The analysis system for the influence of space thruster plume on satellite solar panel mechanics according to claim 8, characterized in that, In module M1: the semi-cone angle α at which the plume begins to enter the solar panel is determined based on the specific installation positions of the thruster and solar panel on the satellite, and β is the known plume influence envelope semi-cone angle. In module M2: the plume force acting on the affected area of ​​the windsurfing can be divided into two components F in the Y and Z directions. Y F Z Each directional component of the force can be decomposed into a feather momentum impact force F. Y动量 F Z动量 and local static pressure F Y压力 F Z压力 : F Y = F Y动量 +F Y压力 F Z = F Z动量 +F Z压力 In module M3: the mass flow rate field and pressure field of the thruster plume are simulated and analyzed using the fluid analysis software Fluent. The mass flow rate field is then integrated circumferentially to obtain a curve showing the percentage of mass flow rate as a function of the plume's half-cone angle. This curve yields the mass flow rate percentage δ within the plume annulus from half-cone angle α to β, which represents the ratio of the plume's momentum impact force to the thruster's rated thrust F. T The ratio; In module M4: based on the size of the affected area on the axial cross-section of the plume field, the corresponding plume center angles θ in the Y and Z directions are obtained. y θ z Thus, a momentum impact force can be obtained: F Y动量 =F T ×δ×θ y / 360 F Z动量 =F T ×δ×θ Z / 360 In module M5: the static pressure is obtained based on the plume pressure field and the area of ​​the region on the sail affected by the plume in the corresponding direction. F Y压力 =P L ×A Y F Z压力 =P L ×A Z Among them, P L For the local static pressure, A Y A Z The area affected in the corresponding direction; The module M6 includes: Module M6.1: Calculate the resultant force of the plume impact: F Y = F Y动量 +F Y压力 F Z = F Z动量 +F Z压力 Module M6.2: Calculate the torque of the plume force on the three coordinate axes of the satellite's center of mass based on the distance of the affected area from the satellite's center of mass; Module M6.3: Combined with the thruster's operating mode, the corresponding angular momentum can be obtained.

10. A space thruster, characterized in that, An analysis system for the impact of space thruster plumes on satellite solar panels, as described in claim 8.

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