Method and system for long-term residence of a geocentric polar levitating spacecraft

Abstract

The application provides a long-term residence method and system of an earth-pole-suspension spacecraft, and relates to the technical field of spaceflight, and comprises the following steps: S1, a graphene film sail surface is arranged for the earth-pole-suspension spacecraft, the graphene film sail surface is used for interacting with the sunlight, and a suspension centripetal force is calculated; S2, a control system is arranged, the included angle relationship between the graphene film sail surface and the sunlight is controlled according to the suspension centripetal force, the requirement of a suspension orbit is satisfied in real time, a spiral suspension orbit operation is formed, the earth revolves around the sun, one-year return is formed, and the earth-pole-suspension orbit operation of the next cycle is continued. The application can effectively improve the comprehensive detection performance and observation efficiency of the polar spacecraft.

Description

TECHNICAL FIELD

[0001] The present application relates to the field of aerospace technology, in particular to a method and system for long-term residence of a geocentric polar suspended spacecraft. BACKGROUND

[0002] Conventional near-earth artificial spacecraft is affected by the earth's gravity, and its orbit is a near-circular or large-elliptical orbit around the earth's center. The orbit characteristic is that the spacecraft orbit plane passes through the earth's center, and through periodic motion of the orbit, the spacecraft performs periodic interval observation, communication and other tasks on the ground. For observation, communication and other tasks at the north and south poles, currently, polar orbit spacecraft with an orbit inclination close to 90 degrees or sun-synchronous orbit spacecraft are mainly used to achieve short-term observation, communication and other tasks per orbit in the polar region. This is quite disadvantageous for countries located in high latitude regions. Therefore, Russia has proposed a Molniya "lightning" orbit. Its characteristic is that through special design of a large-elliptical orbit, a frozen orbit with an orbit inclination of 63.4 degrees is selected to offset the influence of the earth's non-spherical gravity perturbation term, so that the large-elliptical orbit arch line is frozen, and the spacecraft's speed at the far point is much lower than its speed at the near point, which ensures a longer transit time in the latitude region, especially in the polar region, per orbit, to achieve intermittent, longer time observation, communication and other tasks per orbit in the polar region compared with the polar orbit. However, neither the polar orbit, the sun-synchronous orbit spacecraft, nor the Molniya orbit spacecraft can achieve uninterrupted, continuous, long-term observation, communication and other tasks in the polar region.

[0003] In recent years, in order to achieve uninterrupted, continuous, long-term residence of the spacecraft in the polar region, foreign research teams use the huge sail surface of the solar sail and the reflection of sunlight to provide a certain force to offset part of the earth's and solar gravity, so that the spacecraft's orbit plane no longer passes through the earth's center, and the spacecraft flies around in the polar region, thereby realizing a heliocentric polar suspended orbit at the Sun-Earth Lagrange L1 point. Here, the heliocentric is because the spacecraft's orbit is far from the earth, about 1.5 million kilometers, and is affected by the gravity of the sun and the earth. Although the heliocentric polar suspended spacecraft can meet the requirements of uninterrupted, continuous, long-term observation, communication and other tasks in the polar region, the distance of 1.5 million kilometers seriously limits its application performance. SUMMARY

[0004] In view of the defects in the prior art, the present application provides a method and system for long-term residence of a geocentric polar suspended spacecraft.

[0005] According to the method and system for long-term residence of a geocentric polar suspended spacecraft provided by the present application, the scheme is as follows:

[0006] In a first aspect, a method for long-term residence of a geocentric polar suspended spacecraft is provided, and the method comprises:

[0007] Step S1: setting a graphene film sail for the geocentric polar suspended spacecraft, acting on the light of the sun through the graphene film sail, and calculating the suspended centripetal force;

[0008] Step S2: setting a control system, controlling the included angle relationship between the graphene film sail and the sunlight according to the suspended centripetal force, satisfying the suspended orbit requirement in real time, forming a spiral suspended orbit operation, and following the Earth in revolution around the sun to form a one-year return, and continuing the geocentric polar suspended orbit operation in the next cycle.

[0009] Preferably, the step S1 comprises: generating a light action force by the graphene film sail acting on the light of the sun, and forming a suspended centripetal force with the geocentric gravity generated by the Earth to provide a suspended orbit operation:

[0010]

[0011] The suspended centripetal force satisfies the orbit requirement of the set suspended orbit suspended radius and suspended height.

[0012] Preferably, the control system in the step S2 controls the included angle between the graphene film sail and the sunlight, and ensures that the included angle between the geocentric suspended orbit plane and the ecliptic plane satisfies the requirement of the ecliptic-oblique angle 23.5°, and operates on the suspended orbit with a magnitude of 50,000 kilometers away from the polar region of the Earth.

[0013] Preferably, a variable emissivity film is pasted on the graphene film sail, the graphene film sail is reused as a graphene film variable absorptivity, the reflectivity variation law and the absorptivity variation law are adjusted by strategy, an unequal couple is generated, an attitude control moment is formed, and the attitude pointing of the sail is controlled.

[0014] Preferably, the attitude pointing of the sail is controlled by measuring the included angle between the entire plane of the graphene film sail and the sunlight in real time, calculating the angle difference between the included angle and the ecliptic-oblique angle, generating a control strategy according to the angle difference through a control algorithm, and acting on the graphene film sail to make the angle difference 0, so as to ensure that the included angle between the geocentric suspended orbit plane and the ecliptic plane satisfies the requirement of the ecliptic-oblique angle 23.5°.

[0015] Preferably, the included angle between the geocentric suspended orbit plane and the ecliptic plane satisfying the requirement of the ecliptic-oblique angle 23.5° is that the normal line of the geocentric suspended orbit plane is on an inverted circular conical surface with a half-conical angle of 23.5° along the normal line of the ecliptic plane, and rotates in the same direction and at the same speed as the Earth revolution as time elapses.

[0016] Preferably, the graphene film sail is reused as a graphene antenna, which is used as a transmitting and receiving antenna for data and information transmission to the earth.

[0017] Preferably, a thin film solar cell array is pasted on the graphene film sail to generate electric energy to meet the energy needs of the spacecraft.

[0018] In a second aspect, a long-term residence system for a geocentric polar suspended spacecraft is provided, and the system comprises:

[0019] Module M1: providing a graphene film sail for a geocentric polar suspended spacecraft, interacting with sunlight through the graphene film sail, and calculating a suspended centripetal force;

[0020] Module M2: providing a control system to control the angle between the graphene film sail and sunlight to meet the requirements of a suspended orbit in real time, form a spiral suspended orbit, and follow the Earth in its revolution around the Sun to form a one-year cycle, and continue the geocentric polar suspended orbit operation in the next cycle.

[0021] Preferably, the module M1 includes: generating a light action force by interacting with sunlight through the graphene film sail, and forming a suspended centripetal force with the Earth's centripetal force to provide a suspended orbit operation:

[0022]

[0023] The suspended centripetal force meets the requirements of the suspended orbit radius and the suspended height of the suspended orbit;

[0024] The control system in the module M2 controls the angle between the graphene film sail and sunlight to ensure that the angle between the geocentric suspended orbit and the ecliptic plane meets the requirement of the ecliptic angle of 23.5°, and operates on a suspended orbit with a height of about 50,000 kilometers from the polar region of the Earth.

[0025] A variable emissivity film is pasted on the graphene film sail to reuse the graphene film sail as a graphene film variable absorptivity, and by adjusting the reflectivity and absorptivity variation law, an unequal couple is generated to form an attitude control torque for controlling the attitude direction of the sail.

[0026] The control of the attitude direction of the sail is achieved by measuring the angle between the entire plane of the graphene film sail and the sunlight in real time, calculating the angle difference between the angle and the ecliptic angle, and generating a control strategy through a control algorithm according to the angle difference, and acting on the graphene film sail to make the angle difference zero, thereby ensuring that the angle between the geocentric suspended orbit and the ecliptic plane meets the requirement of the ecliptic angle of 23.5°.

[0027] The angle between the geocentric levitation orbit plane and the ecliptic plane satisfies the requirement of 23.5° obliquity of the ecliptic at any given time. The normal of the geocentric levitation orbit plane lies on an inverted cone surface that forms a half-cone angle of 23.5° with the normal of the ecliptic plane. As time passes, it rotates in the same direction and at the same speed as the Earth's revolution.

[0028] The graphene film sail is reused as a graphene antenna, serving as a transmission and reception antenna for transmitting data and information to the ground.

[0029] The graphene film sail is covered with a thin-film solar cell array to generate electricity to supply the energy needs of the spacecraft.

[0030] Compared with the prior art, the present invention has the following beneficial effects:

[0031] 1. The invention has higher application efficiency: The suspended orbit altitude is far below 1.5 million kilometers, which is comparable to the orbit altitude of GEO satellites. This allows the payloads of GEO satellites, such as remote sensing, communication, and navigation, to be successfully applied to the geocentric polar suspended spacecraft of this invention. At the same time, the lower suspension altitude enables uninterrupted, continuous, and long-term observation, communication, and navigation of the polar regions. It also results in higher Earth observation resolution, lower signal attenuation, and faster signal transmission, greatly improving application efficiency.

[0032] 2. The invention provides more power: The graphene film solar sail of the present invention generates more power than that of traditional polar levitation spacecraft. Compared with electric propulsion, it has the advantage of not needing to consume working propellant, which allows it to stay in the polar region continuously and for a long time without interruption. It also revolves around the sun with the earth, forming a cyclic orbit with a designable inner cycle and an outer cycle that is the same as the earth's revolution cycle.

[0033] Other beneficial effects of the present invention will be explained in detail through the introduction of specific technical features and technical solutions in specific embodiments. Those skilled in the art should be able to understand the beneficial technical effects brought about by these technical features and technical solutions through the introduction of these technical features and technical solutions. Attached Figure Description

[0034] 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:

[0035] Figure 1 This is a schematic diagram showing the forces acting on the geocentric levitating spacecraft over a one-year cycle and its spatial position relative to the sun and the earth, provided by the present invention.

[0036] Figure 2 A schematic diagram showing the spatial position of the normal to the suspended orbit over one year;

[0037] Figure 3 This is a schematic diagram of the forces acting on the geocentric levitation spacecraft on the winter solstice in this invention;

[0038] Figure 4 This is a simulation diagram of the annual orbit of the geocentric levitating spacecraft in this invention. Detailed Implementation

[0039] 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 scope of protection of the present invention.

[0040] This invention provides a method for the long-term residence of a geocentric polar levitated spacecraft, enabling the spacecraft to remain suspended and operate at altitudes of approximately 50,000 kilometers above the Earth's North and South Poles, significantly improving the overall detection performance and observation efficiency of polar spacecraft. This invention employs a graphene film as the sail of the geocentric polar levitated spacecraft. Through its interaction with sunlight, compared to traditional polyimide film solar sails, the graphene film sail used in this invention can provide tens to hundreds of times greater light-force, allowing the levitation altitude of the polar levitated spacecraft to be further reduced to the 50,000-kilometer range. Within this spatial range, the gravitational pull of the sun on the spacecraft is far less than that of the Earth. Therefore, the geocentric polar levitated spacecraft is primarily affected by Earth's gravity. The combined force of the light-force generated by the graphene film sail and Earth's gravity forms the centripetal force that enables the spacecraft to continuously operate in a suspended orbit above the Earth's poles.

[0041] Reference Figure 1 As shown, the method specifically includes:

[0042] Step S1: Install graphene film sails on the polar levitation spacecraft. The graphene film sails interact with sunlight to generate a light force, which, together with the Earth's gravity, forms a centripetal force to provide levitation for orbital operation.

[0043]

[0044] The centripetal force of the suspension meets the track requirements for the set suspension radius and suspension height. Among them, the magnitude of the light force is tens to hundreds of times greater than the light pressure generated by traditional polyimide film solar sails.

[0045] Step S2: Set up a control system to control the angle between the graphene film sail and the sunlight according to the centripetal force of suspension, meet the requirements of the suspension track in real time, form a spiral suspension track, and follow the Earth's revolution with the sun to complete the cycle from the winter solstice to the spring equinox, summer solstice, autumn equinox, and back to the winter solstice, forming a yearly cycle, and continue the geocentric polar suspension track operation for the next cycle.

[0046] The control system controls the angle between the graphene film sail and the sunlight in real time, ensuring that the angle between the geocentric suspended orbit plane and the ecliptic plane meets the requirement of 23.5° obliquity of the ecliptic, enabling operation on a suspended orbit at an altitude of approximately 50,000 kilometers above the Earth's polar regions.

[0047] Specifically, a variable emissivity film is attached to the graphene film sail surface, which is then reused as a graphene film with variable absorptivity. By adjusting the variation patterns of reflectivity and absorptivity through strategic methods, unequal large torques are generated, forming attitude control torques to control the attitude and orientation of the sail surface.

[0048] The control of the sail's orientation involves real-time measurement of the angle between the entire plane of the graphene film sail and the sunlight, calculating the angle difference between this angle and the obliquity of the ecliptic. Based on this angle difference, a control algorithm is used to generate a control strategy that is applied to the graphene film sail to ensure that the angle difference is zero, guaranteeing that the angle between the geocentric levitation orbital plane and the ecliptic plane meets the 23.5° obliquity requirement. The 23.5° obliquity requirement is achieved at any given moment when the normal to the geocentric levitation orbital plane lies on an inverted cone forming a 23.5° semi-cone angle with the normal to the ecliptic plane. Over time, the orbit rotates in the same direction and at the same speed as the Earth's revolution around the sun. Figure 2 As shown.

[0049] Graphene film sails can be reused as graphene antennas, serving as both transmission and reception antennas for transmitting data and information to the ground.

[0050] Thin-film solar cell arrays are attached to the graphene film sail to generate electricity to power the spacecraft.

[0051] Reference Figure 3As shown, on the winter solstice, the normal to the geocentric levitation orbit plane coincides with the Earth's rotation axis. Through control algorithms, the angle between the sail and sunlight is adjusted so that the combined force of the light force on the spacecraft's sail and Earth's gravity—that is, the centripetal force—satisfies the orbital requirements of the levitation radius ρ and levitation height h. Over time, the spacecraft uses the control algorithm of the control system to formulate and generate control strategies, continuously controlling the angle between the sail and sunlight to meet the levitation orbit requirements in real time, forming a spiral levitation orbit. Following the Earth's revolution around the sun, it completes a cycle from the winter solstice to the spring equinox, summer solstice, autumn equinox, and back to the winter solstice, forming a yearly cycle, and continues the next cycle of geocentric polar levitation orbit operation. Figure 1 and Figure 4 As shown in the figure. The requirements for the suspension radius ρ and suspension height h of the suspended track are shown in the following formula.

[0052] F 光作用力 ·cosθ2+·F 引力 cosθ1=mρω 2

[0053]

[0054] F 光作用力 sinθ2=F 引力 ·sinθ1

[0055]

[0056] Where G is the gravitational constant, M is the mass of the Earth, m is the mass of the spacecraft, r is the radius of the Earth, θ1 is the angle between the gravitational vector and the orbital plane, θ2 is the angle between the sail and the orbital plane, ω is the angular velocity of the inner suspension circle, and T is the period of the inner suspension circle.

[0057] This invention also provides a long-term residence system for a geocentric polar levitation spacecraft. This system can be implemented by executing the steps of the aforementioned long-term residence method for a geocentric polar levitation spacecraft. That is, those skilled in the art can understand the aforementioned long-term residence method for a geocentric polar levitation spacecraft as a preferred embodiment of the long-term residence system for a geocentric polar levitation spacecraft. The system specifically includes:

[0058] Module M1: Equipped with a graphene film sail for the geocentric polar levitation spacecraft. The graphene film sail interacts with sunlight to generate a photodynamic force, which, together with Earth's gravity, forms the centripetal force necessary for levitation orbital operation.

[0059]

[0060] The centripetal force of the suspension meets the track requirements for the set suspension radius and suspension height. Among them, the magnitude of the light force is tens to hundreds of times greater than the light pressure generated by traditional polyimide film solar sails.

[0061] Module M2: Set up a control system to control the angle between the graphene film sail and the sunlight according to the centripetal force of suspension, meet the requirements of the suspension track in real time, form a spiral suspension track, and follow the Earth's revolution with the sun to complete the cycle from the winter solstice to the spring equinox, summer solstice, autumn equinox, and back to the winter solstice, forming a yearly cycle, and continue the geocentric polar suspension track operation for the next cycle.

[0062] The control system controls the angle between the graphene film sail and the sunlight in real time, ensuring that the angle between the geocentric suspended orbit plane and the ecliptic plane meets the requirement of 23.5° obliquity of the ecliptic, enabling operation on a suspended orbit at an altitude of approximately 50,000 kilometers above the Earth's polar regions.

[0063] Specifically, a variable emissivity film is attached to the graphene film sail surface, which is then reused as a graphene film with variable absorptivity. By adjusting the variation patterns of reflectivity and absorptivity through strategic methods, unequal large torques are generated, forming attitude control torques to control the attitude and orientation of the sail surface.

[0064] The control of the sail's orientation involves real-time measurement of the angle between the entire plane of the graphene film sail and the sunlight, calculating the angle difference between this angle and the obliquity of the ecliptic. Based on this angle difference, a control algorithm is used to generate a control strategy that is applied to the graphene film sail to ensure that the angle difference is zero, guaranteeing that the angle between the geocentric levitation orbital plane and the ecliptic plane meets the 23.5° obliquity requirement. The 23.5° obliquity requirement is achieved at any given moment when the normal to the geocentric levitation orbital plane lies on an inverted cone forming a 23.5° semi-cone angle with the normal to the ecliptic plane. Over time, the orbit rotates in the same direction and at the same speed as the Earth's revolution around the sun. Figure 2 As shown.

[0065] Graphene film sails can be reused as graphene antennas, serving as both transmission and reception antennas for transmitting data and information to the ground.

[0066] Thin-film solar cell arrays are attached to the graphene film sail to generate electricity to power the spacecraft.

[0067] Reference Figure 3As shown, on the winter solstice, the normal to the geocentric suspended orbit plane coincides with the Earth's rotation axis. Through control algorithms, the angle between the sail and sunlight is adjusted so that the combined force of the light force on the spacecraft's sail and Earth's gravity—that is, the centripetal force—satisfies the orbital requirements of the suspended orbit radius ρ and suspended height h. Over time, the spacecraft uses the control algorithm of the control system to formulate and generate control strategies, continuously controlling the angle between the sail and sunlight to meet the suspended orbit requirements in real time, forming a spiral suspended orbit. Following the Earth's revolution around the sun, it completes a cycle from the winter solstice to the spring equinox, summer solstice, autumn equinox, and back to the winter solstice, forming a yearly cycle, and continues the next cycle of geocentric polar suspended orbit operation. Figure 1 and Figure 4 As shown.

[0068] The present invention will now be described in more detail.

[0069] This invention provides a method for long-term residence of a geocentric polar levitated spacecraft, which has the ability to remain suspended and operate over the Earth's North and South Poles for extended periods at altitudes of approximately 50,000 kilometers above the poles. It can be applied to high-resolution, high-efficiency, and high-value polar observation, polar navigation, and polar communication missions, and will effectively improve the comprehensive detection performance and observation efficiency of polar spacecraft.

[0070] This invention includes a graphene film sail that interacts with sunlight to generate a photodynamic force. This force, combined with Earth's gravity, forms a centripetal force that provides the necessary levitation orbit. This centripetal force must meet the orbital requirements for levitation radius and altitude. Simultaneously, a control strategy is developed by the geocentric polar levitation spacecraft control system to control the angle between the graphene film sail and sunlight in real time. This ensures that the angle between the levitation orbit plane and the ecliptic plane meets the obliquity of 23.5°, enabling operation in a levitation orbit at altitudes on the order of 50,000 kilometers above the Earth's polar regions. This method can be applied to high-resolution, high-efficiency, and high-value polar observation, polar navigation, and polar communication missions, effectively improving the overall detection performance and observation efficiency of polar spacecraft.

[0071] The geocentric polar levitated spacecraft includes a graphene film sail, a control system, and payloads for power supply, communication, remote sensing, and navigation. The graphene film sail, fabricated using specific processes, interacts with sunlight and lasers to generate a light-force tens to hundreds of times greater than that of a traditional solar sail, serving as the power source for the geocentric levitated spacecraft without consuming propellant. The control system uses, but is not limited to, a variable reflectivity film to control the spacecraft's attitude, adjusting the angle between the sail and sunlight in real time to ensure the angle between the levitated orbital plane and the ecliptic plane satisfies the obliquity of the ecliptic at 23.5°. The power supply is provided by a flexible solar cell array attached to the film sail, supplying electrical energy to the entire geocentric polar levitated spacecraft. The communication, remote sensing, and navigation payloads include, but are not limited to, Earth observation remote sensing payloads, communication payloads, and navigation payloads applicable to GEO orbit satellites.

[0072] like Figure 3 As shown, on the winter solstice, the levitation height h is 50,000 kilometers, the levitation radius ρ is 3,000 kilometers, the inner levitation cycle is 37.0847 days, and the outer levitation cycle is 1 year. Its trajectory is as follows... Figure 4 As shown.

[0073] in, Figure 3 and Figure 4 In the diagram, 1 represents the Sun; 2 represents the Earth; 21 represents the Earth's equator; 22 represents the Earth's polar regions; 23 represents the Earth's axis of rotation; 3 represents the Earth's polar levitation spacecraft; 31 represents the graphene film sail of the Earth's polar levitation spacecraft; and 32 represents the Earth's polar levitation spacecraft control system.

[0074] This invention provides a method and system for the long-term residence of a geocentric polar levitated spacecraft. Through its interaction with sunlight, it generates a photodynamic force, which, together with Earth's gravity, forms a centripetal force providing a levitated orbit. This centripetal force satisfies the orbital requirements for levitation radius and altitude. Simultaneously, the geocentric polar levitated spacecraft control system formulates a control strategy to control the angle between the graphene film sail and sunlight in real time, ensuring that the angle between the levitated orbital plane and the ecliptic plane meets the obliquity of 23.5°. This allows operation in a levitated orbit at an altitude of approximately 50,000 kilometers above the Earth's polar regions. This technology can be applied to high-resolution, high-efficiency, and high-value polar observation, polar navigation, and polar communication missions, effectively improving the overall detection performance and observation efficiency of polar spacecraft.

[0075] 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.

[0076] 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 long-term residence of a geocentric polar levitation spacecraft, characterized in that, include: Step S1: Install a graphene film sail on the geocentric polar levitation spacecraft, and calculate the centripetal force of levitation by observing the interaction between the graphene film sail and sunlight. Step S2: Set up a control system to control the angle between the graphene film sail and the sunlight according to the centripetal force of suspension, meet the requirements of the suspension track in real time, form a spiral suspension track, and follow the Earth's revolution with the sun to form a yearly return, and continue the geocentric polar suspension track operation for the next cycle. Step S1 includes: generating a light force through the interaction of the graphene film sail surface with sunlight, which, together with the Earth's gravity, forms a levitation centripetal force to provide the levitation orbit for operation. The centripetal force of the suspension meets the track requirements of the set suspension radius and suspension height; In step S2, the control system controls the angle between the graphene film sail and the sunlight to ensure that the angle between the geocentric suspended orbit plane and the ecliptic plane meets the requirement of 23.5° obliquity of the ecliptic, and that it runs on a suspended orbit at an altitude of 50,000 kilometers above the Earth's polar regions. A variable emissivity film is attached to the graphene film sail surface, which is then reused as a graphene film with variable absorptivity. By adjusting the variation patterns of reflectivity and absorptivity through a strategy, unequal large torques are generated, forming attitude control torques to control the attitude and orientation of the sail surface.

2. The method for long-term residence of a geocentric polar levitation spacecraft according to claim 1, characterized in that, The attitude and orientation of the control sail are determined by measuring the angle between the entire plane of the graphene film sail and the sunlight in real time, calculating the angle difference between the angle and the obliquity of the ecliptic, and formulating a control strategy based on the angle difference through a control algorithm. This strategy is applied to the graphene film sail to ensure that the angle difference is 0, thus guaranteeing that the angle between the geocentric levitation orbital plane and the ecliptic plane meets the requirement of an obliquity of the ecliptic of 23.5°.

3. The method for long-term residence of a geocentric polar levitation spacecraft according to claim 2, characterized in that, The angle between the geocentric levitation orbit plane and the ecliptic plane satisfies the requirement of 23.5° obliquity of the ecliptic at any given time. The normal of the geocentric levitation orbit plane lies on an inverted cone surface that forms a 23.5° semi-cone angle with the normal of the ecliptic plane. As time passes, it rotates in the same direction and at the same speed as the Earth's revolution.

4. The method for long-term residence of a geocentric polar levitation spacecraft according to claim 1, characterized in that, The graphene film sail is reused as a graphene antenna, serving as a transmission and reception antenna for transmitting data and information to the ground.

5. The method for long-term residence of a geocentric polar levitation spacecraft according to claim 1, characterized in that, The graphene film sail is covered with a thin-film solar cell array to generate electricity to supply the energy needs of the spacecraft.

6. A long-term residence system for a geocentric polar levitation spacecraft, characterized in that, include: Module M1: Sets up a graphene film sail for the geocentric polar levitation spacecraft, and calculates the centripetal force of levitation by interacting with the sunlight through the graphene film sail; Module M2: Sets up a control system to control the angle between the graphene film sail and the sunlight based on the centripetal force of the suspension, meets the requirements of the suspension track in real time, forms a spiral suspension track, and follows the Earth's revolution with the sun to form a yearly cycle, and continues the geocentric polar suspension track operation for the next cycle. The module M1 includes: generating a light force through the interaction of the graphene film sail surface with sunlight, which, together with the Earth's gravity, forms a levitation centripetal force to provide levitation orbital operation. The centripetal force of the suspension meets the track requirements of the set suspension radius and suspension height; The control system in module M2 controls the angle between the graphene film sail and the sunlight to ensure that the angle between the geocentric suspended orbit plane and the ecliptic plane meets the requirement of 23.5° obliquity of the ecliptic, and that it runs on a suspended orbit at an altitude of 50,000 kilometers above the Earth's polar regions. A variable emissivity film is attached to the graphene film sail surface, which is then reused as a graphene film with variable absorptivity. By adjusting the variation patterns of reflectivity and absorptivity through a strategy, unequal large torques are generated, forming attitude control torques to control the attitude orientation of the sail surface. The attitude and orientation of the control sail are determined by measuring the angle between the entire plane of the graphene film sail and the sunlight in real time, calculating the angle difference between the angle and the obliquity of the ecliptic, and formulating a control strategy based on the angle difference through a control algorithm. This strategy is applied to the graphene film sail to make the angle difference zero, ensuring that the angle between the geocentric levitation orbital plane and the ecliptic plane meets the requirement of 23.5° obliquity of the ecliptic. The angle between the geocentric levitation orbit plane and the ecliptic plane satisfies the requirement of 23.5° obliquity of the ecliptic at any given time. The normal of the geocentric levitation orbit plane lies on an inverted cone surface that forms a half-cone angle of 23.5° with the normal of the ecliptic plane. As time passes, it rotates in the same direction and at the same speed as the Earth's revolution. The graphene film sail is reused as a graphene antenna, serving as a transmission and reception antenna for transmitting data and information to the ground. The graphene film sail is covered with a thin-film solar cell array to generate electricity to supply the energy needs of the spacecraft.

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