Dual-surround detection method and system for Mumour system

Abstract

The invention provides a battle system double-encircling detection method and system, and the method comprises the steps: carrying out the emission in a form of a combination of a polar orbit encircling device and a medium-low inclination angle encircling device, jointly completing the flight from the earth to a battle transfer orbit, carrying out the selective separation of the two encircling devices before approaching a battle, carrying out the capturing, braking and ignition, and enabling the two encircling devices to enter different orbits, the two surrounding devices are each provided with a magnetic field measurement device, an inter-device communication device and a device-ground communication device, the two surrounding devices carry out star magnetic field and gravitational field measurement respectively, a machine is selected to carry out star atmosphere occultation and plasma ring measurement, and when resources are sufficient, the middle-low dip angle surrounding device can adjust a track to carry out ring wood and satellite detection. The star system double-surrounding detection system comprises the links of transfer orbit design, assembly resource analysis, star system inner orbit design, resource analysis, load addition and distribution demonstration, environment-wood-satellite extended task analysis and the like. According to the invention, two surrounding devices can be launched at a time to obtain the star data, the resource utilization rate and the result output are improved, and the engineering value is high.

Description

Technical Field

[0001] The present invention belongs to the technical field of deep space exploration mission design. Specifically, it relates to a method and system for double-orbit exploration of the Jupiter system, especially a method and implementation strategy for double-orbit exploration of the Jupiter system. Background Art

[0002] Deep space exploration refers to the activity of using artificial spacecraft to explore celestial bodies and space beyond the moon. Compared with near-earth exploration, deep space exploration missions have characteristics such as large mission volumes and relatively high technical difficulties.

[0003] Jupiter and the planets beyond it (Saturn, Uranus, Neptune) are gaseous planets, whose compositions are similar to that of the sun, and each has multiple natural satellites. Among them, Jupiter has the largest mass and volume, and also has a large number of Jupiter satellites (hereinafter referred to as "moons"). Conducting exploration of Jupiter and its satellites has great significance in multiple aspects such as science, technology, and economy.

[0004] The opportunities for Jupiter system exploration missions are relatively few, and the resource investment is also limited. So far, there have been 4 exploration missions targeting the Jupiter system implemented internationally, namely: Galileo, Juno, Jupiter Icy Moons Explorer, and Europa Clipper. Among them, Galileo achieved low-inclination orbit around Jupiter and Jupiter atmosphere entry exploration; Juno achieved polar orbit (hereinafter referred to as "polar orbit") around Jupiter; Jupiter Icy Moons Explorer was launched in April 2023 and will achieve low-inclination orbit around Jupiter and orbit around Ganymede; Europa Clipper will be launched in October 2024 and will operate in an orbit with a low inclination around Jupiter to conduct multiple flyby explorations of Europa.

[0005] It can be concluded that the currently implemented Jupiter system exploration missions all adopt the strategy of a single orbiter.

[0006] Both Jupiter and its moons have numerous exploration elements of great scientific value, and there are mutual influences between Jupiter and its satellites. The scientific exploration elements of Jupiter include: magnetic field, gravity field, aurora, atmosphere, Jupiter satellites, etc. For magnetic field and gravity field exploration, data for the entire latitude region need to be obtained, and a polar orbit is more suitable. The aurora is mainly located in the polar regions of Jupiter, and a large-inclination orbit is required. For atmosphere exploration, orbits with different inclinations can be used. For Jupiter satellite exploration, a low-inclination orbit is more suitable.

[0007] The scientific exploration elements of the four Galilean satellites of Jupiter (Io to Callisto) include: internal structure and activity, surface topography, material composition, magnetic field, volcanic activity of Io, subsurface oceans of Europa, Ganymede, and Callisto, etc.

[0008] To detect these elements, a polar orbit around Jupiter's moons is more suitable. The magnetic field is an important element in studying the coupling between Jupiter and its moons. The magnetic field data detected near Europa needs to be decoupled from Jupiter's magnetic field data to accurately obtain Europa's own magnetic field.

[0009] A polar orbiter refers to a polar-orbiting satellite, which is an artificial satellite operating in a polar orbit and plays an important role in meteorology, resource exploration, environmental monitoring and other fields.

[0010] Patent document CN116495196A discloses a method for determining the capture orbit of a deep space exploration spacecraft around Jupiter, which uses the gravitational forces of Jupiter's natural satellites and the sun to change the capture orbit to meet different requirements during the capture process, and can provide a more accurate design scheme for the given desired pericenter radius.

[0011] Patent document CN110450979A discloses a multi-energy and multi-spacecraft combined Jupiter system and planet-crossing detector, including a Jupiter system detector and a planet-crossing detector, which respectively achieve Jupiter system orbiting exploration and planet-crossing exploration, and solve the problem of detector energy selection in different mission scenarios.

[0012] Patent document CN114115330A discloses an orbital design method that takes into account Mars orbiting, entry, and landing exploration. It uses a segmented mission orbit design plus orbit transfer splicing method to achieve Mars exploration orbit design, and solves the problem of comprehensive design of multiple types of orbits for Mars exploration.

[0013] Patent document CN116707611B discloses a multi-objective cooperative control method and device for Mars exploration, which uses a multi-objective cooperative flight control event arrangement and control conflict iteration method to achieve multi-objective flight control, and solves the problem of optimizing the ground flight control strategy when multiple spacecraft are in orbit.

[0014] Patent document CN119443860A discloses a method for analyzing deep space exploration mission-level requirements, which visually expresses and analyzes deep space exploration missions and requirements based on multiple views, and finally gives a mission and requirement model. It solves the problem of analyzing top-level mission requirements for deep space exploration.

[0015] Patent document CN119375916A discloses an inter-satellite measurement system and method for a lunar orbit formation navigation microsatellite, which uses the local timing signals of two satellites respectively to solve the inter-satellite distance and time difference, and solves the problem of inter-satellite measurement between multiple lunar satellites.

[0016] However, the exploration mission of the Jupiter system faces difficulties such as a harsh radiation environment, long communication distances, long mission cycles, and wide-ranging changes in the space environment. Its technical difficulty is relatively higher than that of near-Earth satellites. To ensure the feasibility of the mission project, multiple aspects such as the launch capacity of the launch vehicle, flight orbit, and detector scheme need to be comprehensively considered during the design phase. Summary of the Invention

[0017] Aiming at the defects in the prior art, the purpose of the present invention is to provide a method and system for double-ring exploration of the Jupiter system.

[0018] A double-ring exploration system for the Jupiter system according to the present invention includes two orbiting vehicles. The two orbiting vehicles include two orbiting vehicles: a polar orbiting vehicle and a medium-low inclination orbiting vehicle. The two orbiting vehicles are launched in the form of a combined body and jointly complete the transfer orbit flight between the Earth and Jupiter.

[0019] The polar orbiting vehicle and the medium-low inclination orbiting vehicle each include: a magnetic field measurement payload, an inter-vehicle communication device, and an Earth-vehicle communication device. The polar orbiting vehicle and the medium-low inclination orbiting vehicle can each measure the Jupiter magnetic field and gravity field through the magnetic field measurement payload, and conduct Jupiter atmospheric occultation observation, plasma ring measurement, and inter-satellite ranging through the inter-vehicle communication device. The polar orbiting vehicle and the medium-low inclination orbiting vehicle can communicate independently with the Earth through the Earth-vehicle communication device.

[0020] Preferably, before approaching Jupiter, the two orbiting vehicles first separate according to specific circumstances, then each implement a Jupiter capture braking ignition, and finally enter a medium-low inclination large elliptical orbit around Jupiter and a polar large elliptical orbit around Jupiter respectively.

[0021] When the combined body of the two orbiting vehicles conducts the transfer orbit flight from the Earth to Jupiter, the polar orbiting vehicle adopts a long-term dormancy plus regular wake-up self-check mode, transmits its own information to the medium-low inclination orbiting vehicle, and uses the medium-low inclination orbiting vehicle as the main communication with the Earth. During this period, any orbit corrections are implemented by the medium-low inclination orbiting vehicle.

[0022] The combined body of the two orbiting vehicles separates when entering the sphere of influence of Jupiter's gravity. After separation, orbit corrections are implemented to stagger the times of the Jupiter capture braking ignition of the two orbiting vehicles, so as to ensure that ground measurement and control resources support each orbiting vehicle during its respective braking ignition, and the polar orbiting vehicle and the medium-low inclination orbiting vehicle can be equipped with various types of payloads.

[0023] The double-ring exploration system of the Jupiter system is manufactured according to the design scheme, and the design scheme includes: design of the transfer orbit scheme from the Earth to Jupiter, resource analysis of the combined body of the two orbiting vehicles, design of the inner orbit scheme of the Jupiter system, resource analysis of the two orbiting vehicles, demonstration of additional payloads, and analysis of the extended mission around Jupiter's moons.

[0024] The design of the Earth-to-Jupiter transfer orbit plan specifically refers to designing the Earth-to-Jupiter transfer orbit plan by combining the performance parameters of the preselected launch vehicle, the launch window of the mission requirements, and the constraints of the transfer flight time, and forming a list of Earth-to-Jupiter transfer orbit plans;

[0025] The resource analysis of the two orbiter combination specifically refers to evaluating the resources of the two orbiter combination, and analyzing whether the launch mass meets the mission requirements in combination with the magnitude of the velocity increment and the preliminary selection of the propulsion system;

[0026] The design of the inner-Jupiter system orbit plan specifically refers to designing the inner-Jupiter system exploration orbit plan according to the scientific exploration requirements of the magnetic field and gravity field and the environmental protection constraints of the strong radiation belt of Jupiter, and forming a list of inner-Jupiter system exploration orbit plans;

[0027] The resource analysis of the two orbiters specifically refers to evaluating the resources of the two orbiter combination, and analyzing whether the mass of the two orbiters meets the mission requirements in combination with the magnitude of the velocity increment, the selection of the propulsion system, and the resource requirements of the magnetic field and gravity field detection payloads;

[0028] The demonstration of additional payload specifically refers to evaluating the additional payload, and judging whether there is still available mass margin for the two orbiters after deducting the necessary mass resources;

[0029] The analysis of the extended mission around Jupiter specifically refers to designing the orbit plan of the extended mission around Jupiter in combination with the available mass margin of the medium- and low-inclination orbiter, and forming a list of extended orbits around Jupiter.

[0030] A design system for a double-orbiter exploration system in the Jupiter system according to the present invention includes:

[0031] Module M1: Design of the Earth-to-Jupiter transfer orbit plan, that is, designing the Earth-to-Jupiter transfer orbit plan by combining the performance parameters of the preselected launch vehicle, the launch window of the mission requirements, and the constraints of the transfer flight time, and forming a list of Earth-to-Jupiter transfer orbit plans. Further, the list of Earth-to-Jupiter transfer orbit plans includes: launch window, transfer flight strategy, transfer flight time, velocity increment, launch mass;

[0032] Module M2: Screening of the transfer orbit plan, that is, screening the design results of the Earth-to-Jupiter transfer orbit in combination with the transfer flight time, the magnitude of the velocity increment during the transfer, the mass of the launchable detector, etc. When screening, the preference principle is from high to low as the mass of the launchable detector is large, the velocity increment during the transfer is small, and the transfer flight time is short. Further, the preference principle from high to low specifically means that the preference principle includes a priority value, as shown in the following formula:

[0033] Priority value = launch mass - 0.3 × velocity increment

[0034] The larger the priority value, the better. When the priority values are the same, the solution with a shorter transfer time is preferred. If there are special screening principles, it can be determined according to the specific situation;

[0035] Module M3: Resource evaluation of the two-satellite combination, that is, conduct resource evaluation of the two-satellite combination, combine the magnitude of the velocity increment and the preliminary selection of the propulsion system, and analyze whether the launch mass meets the mission requirements. Whether it meets the mission requirements specifically means that if it meets the mission requirements, transfer to Module M4; if it does not meet the mission requirements, it indicates that the selected launch vehicle and transfer orbit do not support the dual-orbit exploration solution. At this time, it is necessary to determine whether a redesign is required. Further, the need to determine whether a redesign is required specifically means that if the judgment is yes, return to Module M1, and the constraints of the launch vehicle, launch window, and transfer duration tasks can be changed, and then recalculate; if the judgment is no, transfer to Module M11 to end the current mission design;

[0036] Module M4: Design of the exploration orbit plan within the Jupiter system, that is, according to the scientific exploration requirements of the magnetic field and gravitational field and the environmental protection constraints of the strong radiation belt of Jupiter, design the exploration orbit plan within the Jupiter system to form a list of exploration orbit plans within the Jupiter system. Further, the list of exploration orbit plans within the Jupiter system includes: target orbit, velocity increment required for Jupiter capture and orbit adjustment;

[0037] Module M5: Screening of the exploration orbit plan, that is, combine the scientific exploration efficiency to screen the design results of the exploration orbit within the Jupiter system. This module is not a mandatory module and can be skipped depending on the situation;

[0038] Module M6: Resource evaluation of the two satellites, that is, conduct resource evaluation of the two-satellite combination, combine the magnitude of the velocity increment, the selection of the propulsion system, and the resource requirements of the magnetic field and gravitational field detection payloads, and analyze whether the mass of the two satellites meets the mission requirements. Further, whether it meets the mission requirements specifically means that if it meets, transfer to Module M7; if it does not meet, it indicates that the dual-orbit exploration mission is not feasible, transfer to Module M11, and end the current mission design;

[0039] Module M7: Demonstration of the payload augmentation plan, that is, conduct payload augmentation evaluation. After deducting the necessary mass resources, whether there is any available mass margin for the two satellites. If there is a margin, transfer to Module M8; if there is no margin, transfer to Module M9. Among them, whether there is any available mass margin specifically means that, combined with the mass margin of the two satellites, conduct demonstration of the payload augmentation plan to form the scientific objectives and list of the payload augmentation. Further, the scientific objectives and list of the payload augmentation include: payload name, scientific objective, mass, power consumption;

[0040] Module M8: Evaluation of the extended mission of the medium- and low-inclination orbiter, that is, judging whether the extended mission can be carried out from the mass margin. Further, whether the extended mission can be carried out specifically means that if there is a margin, transfer to Module M9; if there is no margin, transfer to Module M10;

[0041] Module M9: Design of the orbit plan for the extended mission around Jupiter, that is, combining the available mass margin of the medium- and low-inclination orbiter, designing the orbit plan for the extended mission around Jupiter, and forming a list of orbit plans for the extended mission around Jupiter. Further, the list of orbit plans for the extended mission around Jupiter includes: target orbit, orbit transfer adjustment, orbit adjustment, and the velocity increment required for target capture;

[0042] Module M10: Organize and form the implementation plan for the dual-orbit exploration of the Jupiter system, that is, organize the results analyzed and designed by Module M9 to form the implementation plan for the dual-orbit exploration of the Jupiter system;

[0043] Module M11: End the current mission design.

[0044] A design method for a dual-orbit exploration system of the Jupiter system provided by the present invention specifically includes the following steps:

[0045] Step S1: Design of the Earth-to-Jupiter transfer orbit plan, that is, combining the performance parameters of the preselected launch vehicle, the launch window required by the mission requirements, and the constraints of the transfer flight time, designing the Earth-to-Jupiter transfer orbit plan, and forming a list of Earth-to-Jupiter transfer orbit plans. Further, the list of Earth-to-Jupiter transfer orbit plans includes: launch window, transfer flight strategy, transfer flight time, velocity increment, and launch mass;

[0046] Step S2: Screening of the transfer orbit plan, that is, combining the transfer flight time, the magnitude of the velocity increment during the transfer process, the mass of the launchable detector, etc., screening the design results of the Earth-to-Jupiter transfer orbit. During screening, the preferred principles from high to low are: large mass of the launchable detector, small velocity increment during the transfer process, and short transfer flight time. Further, the preferred principles from high to low specifically mean that the preferred principles include priority values, as shown in the following formula:

[0047] Priority value = launch mass - 0.3 × velocity increment

[0048] Preferably, the larger the value of the priority value, the better. In the case of the same priority value, preferably select the plan with a short transfer time. If there are special screening principles, it can be determined according to the specific situation;

[0049] Step S3: Resource assessment of the two orbiter combination, that is, conduct resource assessment of the two orbiter combination, analyze whether the launch mass meets the mission requirements in combination with the magnitude of the velocity increment and the preliminary selection of the propulsion system. Whether it meets the mission requirements specifically means that if it meets the mission requirements, go to step S4; if it does not meet the mission requirements, it indicates that the selected launch vehicle and transfer orbit do not support the dual orbiter detection scheme. At this time, it is necessary to judge whether re-design is required. Further, the need to judge whether re-design is required specifically means that if the judgment is yes, return to step S1, and the constraints of the launch vehicle, launch window, and transfer duration tasks can be replaced and recalculated; if the judgment is no, go to step S11 to end the current mission design;

[0050] Step S4: Design of the detection orbit plan within the Jupiter system, that is, design the detection orbit plan within the Jupiter system according to the scientific detection requirements of the magnetic field and gravity field and the environmental protection constraints of the strong radiation belt of Jupiter, and form a list of detection orbit plans within the Jupiter system. Further, the list of detection orbit plans within the Jupiter system includes: target orbit, velocity increment required for Jupiter capture and orbit adjustment;

[0051] Step S5: Screening of the detection orbit plan, that is, screen the design results of the detection orbit within the Jupiter system in combination with the scientific detection efficiency. This step is not a mandatory step and can be skipped depending on the situation;

[0052] Step S6: Resource assessment of the two orbiters, that is, conduct resource assessment of the two orbiter combination, analyze whether the mass of the two orbiters meets the mission requirements in combination with the magnitude of the velocity increment, the selection of the propulsion system, and the resource requirements of the magnetic field and gravity field detection payloads. Further, whether it meets the mission requirements specifically means that if it meets, go to step S7; if it does not meet, it indicates that the dual orbiter detection mission is not feasible, go to step S11, and end the current mission design;

[0053] Step S7: Demonstration of the payload augmentation plan, that is, conduct payload augmentation assessment. After deducting the necessary mass resources, whether there is any available mass margin for the two orbiters. If there is a margin, go to step S8; if there is no margin, go to step S9. Among them, whether there is any available mass margin specifically means that in combination with the mass margin of the two orbiters, conduct demonstration of the payload augmentation plan to form the scientific objectives and list of the payload augmentation. Further, the scientific objectives and list of the payload augmentation include: payload name, scientific objective, mass, power consumption;

[0054] Step S8: Evaluation of the extended mission of the medium and low inclination orbiter, that is, judge whether the extended mission can be carried out from the mass margin. Further, whether the extended mission can be carried out specifically means that if there is a margin, go to step S9; if there is no margin, go to step S10;

[0055] Step S9: Design of the orbiting mission plan around Jupiter, that is, in combination with the available mass margin of the medium- and low-inclination orbiter, design the orbiting mission plan around Jupiter to form a list of orbiting mission plans around Jupiter. Further, the list of orbiting mission plans around Jupiter includes: target orbit, orbit transfer adjustment, orbit adjustment, and the velocity increment required for target capture;

[0056] Step S10: Compile and form the implementation plan for dual orbiting exploration of the Jupiter system, that is, organize the results of the analysis and design in Step S9 to form the implementation plan for dual orbiting exploration of the Jupiter system;

[0057] Step S11: End the design of this mission.

[0058] The present invention also provides a device for dual orbiting exploration of the Jupiter system, which conducts dual orbiting exploration of Jupiter through a polar orbiter and a medium- and low-inclination orbiter, achieving the exploration of the Jupiter atmosphere and the Jupiter plasma torus.

[0059] Compared with the prior art, the present invention has the following beneficial effects:

[0060] 1. The polar orbiter and the medium- and low-inclination orbiter proposed by the present invention can conduct dual orbiting exploration of Jupiter. Each of the two orbiters is equipped with a magnetic field measurement payload, an inter-satellite communication device, and an Earth-satellite communication device, which can not only achieve high-precision measurement of the global magnetic field and gravity field of Jupiter, but also measure the sphere of influence of Jupiter's gravity through inter-satellite measurement, effectively improving the utilization rate of mission resources and the output of scientific achievements.

[0061] 2. The dual orbiting exploration system of the Jupiter system proposed by the present invention includes links such as the design of the Earth-to-Jupiter transfer orbit plan, the resource analysis of the combined body of the two orbiters, the design of the orbiting plan within the Jupiter system, the resource analysis of the two orbiters, the demonstration of additional payloads, and the analysis of the orbiting mission around Jupiter. This system can be widely used in the exploration mission of the Jupiter system, has great engineering reference significance, and is highly feasible.

[0062] 3. The polar orbiter proposed by the present invention adopts a long-term dormancy plus regular wake-up and self-check mode, transmits its own information to the medium- and low-inclination orbiter, and uses the medium- and low-inclination orbiter as the main communication with the ground, thereby reducing the consumption and occupation of on-board resources and ground TT&C resources.

[0063] 4. The present invention proposes to stagger the time of the two orbiters to implement the Jupiter capture braking ignition, so as to ensure that each of the two orbiters is supported by ground TT&C resources during the braking ignition, improving the engineering feasibility of the mission. Description of the Drawings

[0064] By reading the detailed description of the non-limiting embodiments with reference to the following drawings, other features, purposes, and advantages of the present invention will become more obvious:

[0065] Figure 1 Schematic diagram of the double-orbit exploration method for the Jupiter system;

[0066] Figure 2 Schematic diagram of the implementation process of the double-orbit exploration for the Jupiter system;

[0067] As shown in the figure:

[0068] 1 represents the polar orbit orbiter;

[0069] 2 represents the medium-low inclination orbiter;

[0070] 3 represents Jupiter;

[0071] 4 represents the Earth. Specific implementation manner

[0072] The present invention will be described in detail below in conjunction with specific embodiments. The following embodiments will help those skilled in the art to further understand the present invention, but do not limit the present invention in any form. It should be noted that for those of ordinary skill in the art, without departing from the concept of the present invention, several changes and improvements can still be made. These all belong to the protection scope of the present invention.

[0073] The present invention provides a double-orbit exploration system for the Jupiter system. The double-orbit exploration system for the Jupiter system includes two orbiters. The two orbiters include two orbiters: a polar orbit orbiter and a medium-low inclination orbiter. The two orbiters are launched in the form of a combined body and jointly complete the transfer orbit flight between the Earth and Jupiter. The two orbiters can perform double-orbit exploration on Jupiter;

[0074] The polar orbit orbiter and the medium-low inclination orbiter each include: a magnetic field measurement payload, an inter-satellite communication device, and an Earth-satellite communication device; the polar orbit orbiter and the medium-low inclination orbiter can respectively measure the Jupiter magnetic field and gravity field through the magnetic field measurement payload, and carry out Jupiter atmospheric occultation observation, plasma ring measurement, inter-satellite ranging, etc. through the inter-satellite communication device. The polar orbit orbiter and the medium-low inclination orbiter can independently communicate with the Earth through the Earth-satellite communication device.

[0075] Further, before approaching Jupiter, the two orbiters first perform corresponding separation according to specific circumstances, then each perform Jupiter capture braking ignition, and finally enter the medium-low inclination large elliptical orbit around Jupiter and the polar orbit large elliptical orbit around Jupiter respectively.

[0076] Preferably, when the combined body of the two orbiters performs the transfer orbit flight from the Earth to Jupiter, the polar orbit orbiter adopts a long-term dormancy plus regular wake-up self-check mode, transmits its own information to the medium-low inclination orbiter, and mainly communicates with the Earth through the medium-low inclination orbiter, so as to reduce the consumption and occupation of on-board resources and ground measurement and control resources.

[0077] Preferably, when the two orbiter assemblies fly on the Earth-to-Jupiter transfer orbit, the orbit corrections that occur during this period are implemented by the medium-low inclination orbiter.

[0078] Preferably, when the two orbiter assemblies enter the sphere of influence of Jupiter's gravity, they are separated. After separation, orbit corrections are implemented to stagger the times of the two orbiter assemblies performing Jupiter capture braking ignition, so as to ensure that ground measurement and control resources support both orbiter assemblies when they perform braking ignition respectively, and improve the implementability of the mission project.

[0079] Preferably, when resources are sufficient, other types of payloads are added to the polar orbiter and the medium-low inclination orbiter to enrich scientific achievements.

[0080] Preferably, when resources are sufficient, the medium-low inclination orbiter adjusts its orbit to enter the orbit around Jupiter's moon and conducts exploration around Jupiter's moon, further expanding the utilization rate of mission resources and the output of scientific achievements. For example: when resources are sufficient, the medium-low inclination orbiter can adjust its orbit to enter the orbit around Jupiter's moon and conduct dual-orbiter exploration in the Jupiter system.

[0081] The dual-orbiter exploration in the Jupiter system is manufactured according to the design plan, and the design plan includes: design of the Earth-to-Jupiter transfer orbit plan, resource analysis of the two orbiter assemblies, design of the orbits within the Jupiter system, resource analysis of the two orbiters, demonstration of additional payloads, analysis of the extended mission around Jupiter's moon, and other links.

[0082] Among them, the design of the Earth-to-Jupiter transfer orbit plan specifically refers to combining the performance parameters of the preselected launch vehicle, the launch window required by the mission requirements, and the transfer flight time and other constraints to conduct the design of the Earth-to-Jupiter transfer orbit plan, and form a list of Earth-to-Jupiter transfer orbit plans.

[0083] The resource analysis of the two orbiter assemblies specifically refers to conducting a resource assessment of the two orbiter assemblies, and combining the magnitude of the velocity increment and the preliminary selection of the propulsion system to analyze whether the launch mass meets the mission requirements.

[0084] The design of the orbits within the Jupiter system specifically refers to conducting the design of the exploration orbits within the Jupiter system according to the scientific exploration requirements such as the magnetic field and gravity field and the environmental protection constraints of Jupiter's strong radiation belt, and forming a list of exploration orbits within the Jupiter system. For example, setting the perijove altitude at 5000 km and setting the apojove outside the orbit of Jupiter's moon Callisto. This design can not only shorten the time required for the two orbiters to fly through Jupiter's strong radiation belt, but also reduce the damage caused by Jupiter's strong radiation environment to the orbiters.

[0085] The analysis of the resources of the two orbiters specifically refers to evaluating the resources of the two-orbiter combination, and analyzing whether the mass of the two orbiters meets the mission requirements in combination with the magnitude of the velocity increment, the selection of the propulsion system, and the resource requirements of the magnetic field and gravity field detection payloads.

[0086] The demonstration of the additional payload specifically refers to evaluating the additional payload, and judging whether there is any available mass margin for the two orbiters after deducting the necessary mass resources.

[0087] The analysis of the extended mission around Jupiter specifically refers to designing the orbit plan for the extended mission around Jupiter in combination with the available mass margin of the medium- and low-inclination orbiters, and forming a list of extended orbit plans around Jupiter.

[0088] The present invention provides a design system for a double-orbiter detection system in the Jupiter system, including:

[0089] Module M1: Design of the Earth-to-Jupiter transfer orbit plan, that is, in combination with the performance parameters of the preselected launch vehicle, the launch window and transfer flight time required by the mission, etc., design the Earth-to-Jupiter transfer orbit plan, and form a list of Earth-to-Jupiter transfer orbit plans;

[0090] Furthermore, the list of Earth-to-Jupiter transfer orbit plans in Module M1 includes: launch window, transfer flight strategy, transfer flight time, velocity increment, launch mass, as shown in the following table:

[0091] Serial number Transfer flight strategy Launch window Transfer time Velocity increment Launch mass 1 Venus-Earth-Earth 2029.12 6.17 years 0.1 km / s 4900 kg 2 Earth-Earth 2029.07 6.92 years 0.6 km / s 4450 kg 3 Venus-Earth 2031.07 4.34 years 0.7 km / s 4400 kg

[0092] Module M2: Screening of the transfer orbit plan, that is, in combination with the transfer flight time, the magnitude of the velocity increment during the transfer, the mass of the launchable detector, etc., screen the design results of the Earth-to-Jupiter transfer orbit; during screening, the preferred principles from high to low are a large mass of the launchable detector, a small velocity increment during the transfer, and a short transfer flight time;

[0093] Furthermore, the preferred principles from high to low in Module M2 specifically refer to that the preferred principles include priority values, as shown in the following formula:

[0094] Priority value = launch mass - 0.3 × velocity increment

[0095] Preferably, the larger the value of the priority value, the better. In the case of the same priority value, a plan with a short transfer time is preferred; if there are special screening principles, it can be determined according to the specific situation.

[0096] Module M3: Evaluation of the resources of the two-orbiter combination, that is, evaluate the resources of the two-orbiter combination, and analyze whether the launch mass meets the mission requirements in combination with the magnitude of the velocity increment and the preliminary selection of the propulsion system.

[0097] Further, whether the task requirements are met in module M3 specifically means that if the task requirements are met, transfer to module M4; if the task requirements are not met, it indicates that the selected launch vehicle and transfer orbit do not support the dual-orbit exploration plan. At this time, it is necessary to determine whether a redesign is required;

[0098] Further, the need to determine whether a redesign is required specifically means that if the determination is yes, return to module M1, where task constraints such as the launch vehicle, launch window, and transfer duration can be changed, and then recalculated; if the determination is no, transfer to module M11 to end the current task design;

[0099] Module M4: Design of the exploration orbit plan within the Jupiter system, that is, based on scientific exploration requirements such as the magnetic field and gravitational field, and environmental protection constraints of Jupiter's strong radiation belt, design the exploration orbit plan within the Jupiter system to form a list of exploration orbit plans within the Jupiter system;

[0100] Further, the list of exploration orbit plans within the Jupiter system in module M4 includes: target orbit, velocity increment required for Jupiter capture and orbit adjustment, as shown in the following table:

[0101]

[0102] Module M5: Screening of the exploration orbit plan, that is, combining the scientific exploration efficiency, screen the design results of the exploration orbit within the Jupiter system. This module is a non-mandatory module and can be skipped depending on the situation;

[0103] Module M6: Resource assessment of the two orbiters, that is, conduct a resource assessment of the two-orbiter combination, and analyze whether the mass of the two orbiters meets the task requirements in combination with the magnitude of the velocity increment, the selection of the propulsion system, and the resource requirements of the magnetic field and gravitational field detection payloads;

[0104] Further, whether the task requirements are met in module M6 specifically means that if they are met, transfer to module M7; if not, it indicates that the dual-orbit exploration task is not feasible, transfer to module M11, and end the current task design;

[0105] Module M7: Demonstration of the payload augmentation plan, that is, conduct an assessment of the payload augmentation. After deducting the necessary mass resources, whether there is any available mass margin for the two orbiters. If there is a margin, transfer to module M8; if there is no margin, transfer to module M9;

[0106] Among them, whether there is any available mass margin specifically means that in combination with the mass margin of the two orbiters, conduct a demonstration of the payload augmentation plan to form the scientific objectives and list of the payload augmentation;

[0107] Further, the scientific objectives and list of the payload augmentation include: payload name, scientific objective, mass, power consumption, as shown in the following table:

[0108] Serial number Payload Scientific objective Mass Power consumption Remarks 1 Extreme ultraviolet spectral imager Jupiter aurora 8 kg 15W 2 Magnetospheric particle detector Magnetic field, environment 5 kg 20W 3 High-resolution camera Surveying and mapping 5 kg 15W 4 Infrared spectrometer Composition 13 kg 35W

[0109] Module M8: Evaluation of the extended mission of the medium- and low-inclination orbiter, that is, judging whether the extended mission can be carried out from the mass margin;

[0110] Further, whether the extended mission can be carried out in Module M8 specifically means that if there is a margin, it will transfer to Module M9; if there is no margin, it will transfer to Module M10;

[0111] Module M9: Design of the orbit plan for the extended mission around Jupiter, that is, combining the available mass margin of the medium- and low-inclination orbiter to design the orbit plan for the extended mission around Jupiter, and forming a list of orbit plans for the extended mission around Jupiter;

[0112] Further, the list of orbit plans for the extended mission around Jupiter in Module M9 includes: target orbit, orbit transfer adjustment, orbit adjustment, and velocity increment required for target capture, as shown in the following table:

[0113] Serial number Target orbit Orbit transfer strategy Velocity increment Remarks 1 300 km inclination 90° orbit around Europa Maneuver + Jupiter gravity assist + Capture braking 1.5 km / s 2 50 km inclination 90° orbit around Ganymede Maneuver + Jupiter gravity assist + Capture braking 2.1 km / s

[0114] Module M10: Sort out and form the implementation plan for the double-orbit exploration of the Jupiter system, that is, sort out the results analyzed and designed in Module M9 to form the implementation plan for the double-orbit exploration of the Jupiter system;

[0115] Module M11: End the current mission design.

[0116] The present invention proposes a design method for a double-orbit exploration system of the Jupiter system, which specifically includes the following steps:

[0117] Step S1: Design of the Earth-to-Jupiter transfer orbit plan, that is, combining the performance parameters of the preselected launch vehicle, the launch window required by the mission requirements, the transfer flight time, etc., to design the Earth-to-Jupiter transfer orbit plan, and forming a list of Earth-to-Jupiter transfer orbit plans;

[0118] Further, the list of Earth-to-Jupiter transfer orbit plans in Step S1 includes: launch window, transfer flight strategy, transfer flight time, velocity increment, launch mass, as shown in the following table:

[0119] Serial number Transfer flight strategy Launch window Transfer time Velocity increment Launch mass 1 Venus-Earth-Earth 2029.12 6.17 years 0.1 km / s 4900 kg 2 Earth-Earth 2029.07 6.92 years 0.6 km / s 4450 kg 3 Venus-Earth 2031.07 4.34 years 0.7 km / s 4400 kg

[0120] Step S2: Screening of the transfer orbit plan, that is, combining the transfer flight time, the magnitude of the velocity increment during the transfer, the mass of the launchable detector, etc., to screen the design results of the Earth-to-Jupiter transfer orbit; when screening, the preferred principles from high to low are: large mass of the launchable detector, small velocity increment during the transfer, and short transfer flight time;

[0121] Further, the preference principles in step S2, from high to low, specifically refer to that the preference principles include a priority value, as shown in the following formula:

[0122] Priority value = launch mass - 0.3 × velocity increment

[0123] Preferably, the larger the value of the priority value, the better. In the case of the same priority value, the scheme with a shorter transfer time is preferred; if there are special screening principles, it can be determined according to the specific situation;

[0124] Step S3: Evaluation of the resources of the two orbiter combination, that is, conduct an evaluation of the resources of the two orbiter combination, and analyze whether the launch mass meets the mission requirements in combination with the magnitude of the velocity increment and the preliminary selection of the propulsion system;

[0125] Further, whether it meets the mission requirements in step S3 specifically means that if it meets the mission requirements, go to step S4; if it does not meet the mission requirements, it means that the selected launch vehicle and transfer orbit do not support the dual-orbiter detection scheme. At this time, it is necessary to judge whether it is necessary to redesign;

[0126] Further, the need to judge whether it is necessary to redesign specifically means that if the judgment is yes, return to step S1, and the mission constraints such as the launch vehicle, launch window, and transfer duration can be changed, and then recalculate; if the judgment is no, go to step S11 to end this mission design;

[0127] Step S4: Design of the exploration orbit scheme within the Jupiter system, that is, design the exploration orbit scheme within the Jupiter system according to scientific exploration requirements such as magnetic field and gravitational field and the environmental protection constraints of the strong radiation belt of Jupiter, and form a list of exploration orbit schemes within the Jupiter system;

[0128] Further, the list of exploration orbit schemes within the Jupiter system in step S4 includes: target orbit, velocity increment required for Jupiter capture and orbit adjustment, as shown in the following table:

[0129]

[0130] Step S5: Screening of the exploration orbit scheme, that is, screen the design results of the exploration orbit within the Jupiter system in combination with the scientific exploration efficiency. This step is not a mandatory step and can be skipped depending on the situation;

[0131] Step S6: Evaluation of the resources of the two orbiters, that is, conduct an evaluation of the resources of the two orbiter combination, and analyze whether the mass of the two orbiters meets the mission requirements in combination with the magnitude of the velocity increment, the selection of the propulsion system, and the resource requirements of the magnetic field and gravitational field detection payloads;

[0132] Further, whether the task requirements are met in step S6 specifically means that if they are met, proceed to step S7; if not, it indicates that the dual-orbiting detection task is not feasible, then proceed to step S11 to end the current task design.

[0133] Step S7: Demonstrate the payload augmentation plan, that is, conduct an assessment of payload augmentation. After deducting the necessary mass resources, check whether there is any available mass margin for the two orbiters. If there is a margin, proceed to step S8; if there is no margin, proceed to step S9.

[0134] Among them, whether there is any available mass margin specifically means that, in combination with the mass margins of the two orbiters, demonstrate the payload augmentation plan to form the scientific objectives and list of payload augmentation.

[0135] Further, the scientific objectives and list of payload augmentation include: payload name, scientific objective, mass, and power consumption, as shown in the following table:

[0136] Serial number Payload Scientific objective Mass Power consumption Remarks 1 Extreme ultraviolet spectral imager Jupiter aurora 8 kg 15W 2 Magnetospheric particle detector Magnetic field, environment 5 kg 20W 3 High-resolution camera Surveying and mapping 5 kg 15W 4 Infrared spectrometer Composition 13 kg 35W

[0137] Step S8: Evaluate the extended mission of the medium- and low-inclination orbiter, that is, determine whether the extended mission can be carried out based on the mass margin.

[0138] Further, whether the extended mission can be carried out in step S8 specifically means that if there is a margin, proceed to step S9; if there is no margin, proceed to step S10.

[0139] Step S9: Design the orbit plan for the extended mission around Jupiter, that is, in combination with the available mass margin of the medium- and low-inclination orbiter, design the orbit plan for the extended mission around Jupiter to form a list of extended orbit plans around Jupiter.

[0140] Further, the list of extended orbit plans around Jupiter in step S9 includes: target orbit, orbit transfer adjustment, orbit adjustment, and the velocity increment required for target capture, as shown in the following table:

[0141] Serial number Target orbit Orbit transfer strategy Velocity increment Remarks 1 300 km inclination 90° orbit around Europa Maneuver + Jupiter gravity assist + Capture braking 1.5 km / s 2 50 km inclination 90° orbit around Ganymede Maneuver + Jupiter gravity assist + Capture braking 2.1 km / s

[0142] Step S10: Compile and form the implementation plan for the dual-orbiting detection of the Jupiter system, that is, organize the results analyzed and designed in step S9 to form the implementation plan for the dual-orbiting detection of the Jupiter system.

[0143] Step S11: End the current task design.

[0144] The present invention proposes a dual-orbiting detection device for the Jupiter system, which conducts dual-orbiting detection of Jupiter through a polar orbiter and a medium- and low-inclination orbiter, achieving the detection of Jupiter's atmosphere and Jupiter's plasma ring.

[0145] The present invention also provides a Jupiter system dual-orbiting detection system, which can be implemented by executing the process steps of the Jupiter system dual-orbiting detection method. That is, those skilled in the art can understand the Jupiter system dual-orbiting detection method as a preferred embodiment of the Jupiter system dual-orbiting detection system.

[0146] The specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the above specific embodiments, and those skilled in the art can make various changes or modifications within the scope of the claims, which does not affect the essence of the present invention. Without conflict, the embodiments of the present application and the features in the embodiments can be combined arbitrarily with each other.

Claims

1. A double-ring exploration system for the Jupiter system, characterized in that, It includes two orbiters, and the two orbiters include two types of orbiters: a polar orbiter and a medium-low inclination orbiter. The two orbiters are launched in a combined form and jointly complete the transfer orbit flight between the Earth and Jupiter.

2. The Jupiter system double-ring detection system according to claim 1, wherein The polar orbiter and the medium-low inclination orbiter each include: a magnetic field measurement payload, an inter-satellite communication device, and an Earth-satellite communication device. The polar orbiter and the medium-low inclination orbiter can each measure the Jupiter magnetic field and gravity field through the magnetic field measurement payload, and conduct Jupiter atmospheric occultation observation, plasma ring measurement, and inter-satellite ranging through the inter-satellite communication device. The polar orbiter and the medium-low inclination orbiter can communicate independently with the Earth through the Earth-satellite communication device.

3. The Jupiter system dual-orbiting detection system according to claim 1, wherein Before approaching Jupiter, the two orbiters first separate according to specific circumstances, then each performs a Jupiter capture braking ignition, and finally enters the medium-low inclination large elliptical Jupiter orbit and the polar large elliptical Jupiter orbit respectively.

4. The double-ring detection system for the Jupiter system according to claim 1, wherein When the combined body of the two orbiters performs the transfer orbit flight from the Earth to Jupiter, the polar orbiter adopts a long-term dormancy plus regular wake-up self-check mode, transmits its own information to the medium-low inclination orbiter, and uses the medium-low inclination orbiter as the main communication with the Earth. During this period, the orbit correction is implemented by the medium-low inclination orbiter.

5. The double-ring detection system for the Jupiter system according to claim 1, characterized in that, The combined body of the two orbiters separates when entering the sphere of influence of Jupiter's gravity. After separation, an orbit correction is implemented to stagger the time of the Jupiter capture braking ignition of the two orbiters, so as to ensure that both orbiters are supported by ground measurement and control resources when each performs the braking ignition, and the polar orbiter and the medium-low inclination orbiter can be equipped with various types of payloads.

6. The dual-orbiting exploration system of the Jupiter system according to claim 1, wherein It is manufactured according to the design scheme, and the design scheme includes: the design of the Earth-Jupiter transfer orbit scheme, the resource analysis of the combined body of the two orbiters, the design of the inner-Jupiter system orbit scheme, the resource analysis of the two orbiters, the demonstration of additional payloads, and the analysis of the extended mission around Jupiter's moons.

7. The Jupiter system dual-orbit exploration system according to claim 6, wherein The design of the Earth-Jupiter transfer orbit scheme specifically refers to combining the performance parameters of the preselected launch vehicle, the launch window of the mission requirements, and the constraints of the transfer flight time to design the Earth-Jupiter transfer orbit scheme and form a list of Earth-Jupiter transfer orbit schemes; The resource analysis of the combined body of the two orbiters specifically refers to evaluating the resources of the combined body of the two orbiters, and analyzing whether the launch mass meets the mission requirements in combination with the magnitude of the velocity increment and the preliminary selection of the propulsion system; The design of the inner-Jupiter system orbit scheme specifically refers to designing the inner-Jupiter system exploration orbit scheme according to the scientific exploration requirements of the magnetic field and gravity field and the environmental protection constraints of Jupiter's strong radiation belt, and forming a list of inner-Jupiter system exploration orbit schemes; The resource analysis of the two orbiters specifically refers to evaluating the resources of the combined body of the two orbiters, and analyzing whether the masses of the two orbiters meet the mission requirements in combination with the magnitude of the velocity increment, the selection of the propulsion system, and the resource requirements of the magnetic field and gravity field detection payloads; The demonstration of additional payloads specifically refers to evaluating the addition of payloads, and judging whether there is any available mass margin for the two orbiters after deducting the necessary mass resources; The analysis of the extended mission around Jupiter specifically refers to designing the orbital plan for the extended mission around Jupiter by combining the available mass margin of the medium- and low-inclination orbiter, and forming a list of extended mission orbital plans around Jupiter.

8. A design system for the Jupiter system double-orbit exploration system according to any one of claims 1 to 7, characterized in that, Including: Module M1: Design of the Earth-to-Jupiter transfer orbit plan, that is, designing the Earth-to-Jupiter transfer orbit plan by combining the performance parameters of the preselected launch vehicle, the launch window required by the mission, and the constraints of the transfer flight time, and forming a list of Earth-to-Jupiter transfer orbit plans. Further, the list of Earth-to-Jupiter transfer orbit plans includes: launch window, transfer flight strategy, transfer flight time, velocity increment, and launch mass. Module M2: Screening of the transfer orbit plan, that is, screening the design results of the Earth-to-Jupiter transfer orbit by combining the transfer flight time, the magnitude of the velocity increment during the transfer, the mass of the launchable detector, etc. During the screening, the preferred principles from high to low are a large mass of the launchable detector, a small velocity increment during the transfer, and a short transfer flight time. Further, the preferred principles from high to low specifically mean that the preferred principles include priority values, as shown in the following formula: Priority value = launch mass - 0.3×velocity increment The larger the value of the priority value, the better. In the case of the same priority value, a plan with a short transfer time is preferred. If there are special screening principles, it can be determined according to the specific situation. Module M3: Resource assessment of the two-orbiter combination, that is, conducting a resource assessment of the two-orbiter combination, and analyzing whether the launch mass meets the mission requirements by combining the magnitude of the velocity increment and the preliminary selection of the propulsion system. Whether it meets the mission requirements specifically means that if it meets the mission requirements, transfer to Module M4; if it does not meet the mission requirements, it means that the selected launch vehicle and transfer orbit do not support the dual-orbiter detection plan. At this time, it is necessary to judge whether it is necessary to redesign. Further, whether it is necessary to judge whether it is necessary to redesign specifically means that if the judgment is yes, return to Module M1, and the constraints of the launch vehicle, launch window, and transfer duration task can be changed, and then recalculated; if the judgment is no, transfer to Module M11 to end the current mission design. Module M4: Design of the detection orbit plan within the Jupiter system, that is, designing the detection orbit plan within the Jupiter system according to the scientific detection requirements of the magnetic field and gravity field and the environmental protection constraints of the strong radiation belt of Jupiter, and forming a list of detection orbit plans within the Jupiter system. Further, the list of detection orbit plans within the Jupiter system includes: target orbit, velocity increment required for Jupiter capture and orbit adjustment. Module M5: Screening of the detection orbit plan, that is, screening the design results of the detection orbit within the Jupiter system by combining the scientific detection efficiency. This module is not a mandatory module and can be skipped depending on the situation. Module M6: Resource assessment of the two orbiters, that is, conducting a resource assessment of the two-orbiter combination, and analyzing whether the mass of the two orbiters meets the mission requirements by combining the magnitude of the velocity increment, the selection of the propulsion system, and the requirements for the resources of the magnetic field and gravity field detection payload. Further, whether it meets the mission requirements specifically means that if it meets, transfer to Module M7; if it does not meet, it means that the dual-orbiter detection mission is not feasible, and transfer to Module M11 to end the current mission design. Module M7: Demonstration of Payload Enhancement Plan, that is, conduct an assessment of payload enhancement. After deducting the necessary mass resources, check if there is any available mass margin for the two orbiters. If there is a margin, proceed to Module M8; if there is no margin, proceed to Module M9. Specifically, the determination of whether there is available mass margin means conducting a demonstration of the payload enhancement plan in combination with the mass margins of the two orbiters, formulating the scientific objectives and list of payload enhancement. Further, the scientific objectives and list of payload enhancement include: payload name, scientific objective, mass, and power consumption. Module M8: Assessment of the Extended Mission of the Medium-Low Inclination Orbiter, that is, determine whether the extended mission can be carried out based on the mass margin. Further, the determination of whether the extended mission can be carried out specifically means that if there is a margin, proceed to Module M9; if there is no margin, proceed to Module M10. Module M9: Design of the Orbit Plan for the Extended Mission around Jupiter, that is, design the orbit plan for the extended mission around Jupiter in combination with the available mass margin of the medium-low inclination orbiter, forming a list of orbit plans for the extended mission around Jupiter. Further, the list of orbit plans for the extended mission around Jupiter includes: target orbit, orbit transfer adjustment, velocity increment required for orbit adjustment and target capture. Module M10: Compile and Formulate the Implementation Plan for Dual-Orbiter Exploration of the Jupiter System, that is, organize and compile the results of the analysis and design in Module M9 to form the implementation plan for dual-orbiter exploration of the Jupiter System. Module M11: End the current mission design.

9. A design method for the Jupiter system double - loop detection system according to any one of claims 1 to 7, characterized in that, Specifically, it includes the following steps: Step S1: Design of the Earth-to-Jupiter Transfer Orbit Plan, that is, design the Earth-to-Jupiter transfer orbit plan in combination with the performance parameters of the preselected launch vehicle, the launch window required by the mission requirements, and the constraints of the transfer flight time, forming a list of Earth-to-Jupiter transfer orbit plans. Further, the list of Earth-to-Jupiter transfer orbit plans includes, but is not limited to: launch window, transfer flight strategy, transfer flight time, velocity increment, and launch mass. Step S2: Screening of the Transfer Orbit Plan, that is, screen the design results of the Earth-to-Jupiter transfer orbit in combination with the transfer flight time, the magnitude of the velocity increment during the transfer process, the mass of the launchable detector, etc. During the screening, the preferred principles from high to low are a large mass of the launchable detector, a small velocity increment during the transfer process, and a short transfer flight time. Further, the preferred principles from high to low specifically mean that the preferred principles include priority values, as shown in the following formula: Priority value = launch mass - 0.3 × velocity increment Preferably, the larger the value of the priority value, the better. In the case of the same priority value, prefer the plan with a short transfer time. If there are special screening principles, it can be determined according to the specific situation. Step S3: Resource assessment of the two orbiter combination, that is, conduct resource assessment of the two orbiter combination, analyze whether the launch mass meets the mission requirements in combination with the magnitude of the velocity increment and the preliminary selection of the propulsion system. Whether it meets the mission requirements specifically means that if it meets the mission requirements, go to step S4; if it does not meet the mission requirements, it indicates that the selected launch vehicle and transfer orbit do not support the dual-orbiter exploration plan. At this time, it is necessary to judge whether it is necessary to re-design. Further, the judgment of whether it is necessary to re-design specifically means that if the judgment is yes, return to step S1, and the constraints of the launch vehicle, launch window, and transfer duration tasks can be changed, and then recalculate; if the judgment is no, go to step S11 to end this mission design; Step S4: Design of the exploration orbit plan within the Jupiter system, that is, according to the scientific exploration requirements of the magnetic field and gravity field and the environmental protection constraints of the strong radiation belt of Jupiter, design the exploration orbit plan within the Jupiter system to form a list of exploration orbit plans within the Jupiter system. Further, the list of exploration orbit plans within the Jupiter system includes, but is not limited to: target orbit, velocity increment required for Jupiter capture and orbit adjustment; Step S5: Screening of the exploration orbit plan, that is, combine the scientific exploration efficiency to screen the design results of the exploration orbit within the Jupiter system. This step is not a mandatory step and can be skipped depending on the situation; Step S6: Resource assessment of the two orbiters, that is, conduct resource assessment of the two orbiter combination, analyze whether the mass of the two orbiters meets the mission requirements in combination with the magnitude of the velocity increment, the selection of the propulsion system, and the resource requirements of the magnetic field and gravity field detection payloads. Whether it meets the mission requirements specifically means that if it meets, go to step S7; if it does not meet, it indicates that the dual-orbiter exploration mission is not feasible, go to step S11, and end this mission design; Step S7: Demonstration of the payload augmentation plan, that is, conduct payload augmentation assessment. After deducting the necessary mass resources, whether there is still available mass margin for the two orbiters. If there is a margin, go to step S8; if there is no margin, go to step S9. Among them, whether there is still available mass margin specifically means that in combination with the mass margin of the two orbiters, conduct demonstration of the payload augmentation plan to form the scientific objectives and list of the payload augmentation. Further, the scientific objectives and list of the payload augmentation include, but are not limited to: payload name, scientific objective, mass, power consumption; Step S8: Assessment of the extended mission of the medium-low inclination orbiter, that is, judge whether the extended mission can be carried out from the mass margin. Further, whether the extended mission can be carried out specifically means that if there is a margin, go to step S9; if there is no margin, go to step S10; Step S9: Design of the extended mission orbit plan around Jupiter's moons, that is, in combination with the available mass margin of the medium-low inclination orbiter, design the extended mission orbit plan around Jupiter's moons to form a list of extended mission orbits around Jupiter's moons. Further, the list of extended mission orbits around Jupiter's moons includes, but is not limited to: target orbit, orbit transfer adjustment, velocity increment required for orbit adjustment and target capture; Step S10: Organize and form the implementation plan for the dual-orbit exploration of the Jupiter system, that is, organize the results of the analysis and design in Step S9 to form the implementation plan for the dual-orbit exploration of the Jupiter system; Step S11: End the design of this mission.

10. A double-ring exploration device for the Jupiter system, characterized in that, By using the dual-orbit exploration system of the Jupiter system described in any one of claims 1 to 7, the dual-orbit exploration of Jupiter is carried out through a polar orbiter and a medium-low inclination orbiter, realizing the exploration of the Jupiter atmosphere and the Jupiter plasma ring.

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