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

Abstract

The invention provides a long-term residence method and system for an earth-centered polar region suspension spacecraft, and relates to the technical field of spaceflight, and the method comprises the steps: S1, setting a graphene film sail surface for the earth-centered polar region suspension spacecraft, enabling the graphene film sail surface to act with the light of the sun, and calculating the suspension centripetal force; and S2, a control system is arranged, the included angle relation between the graphene film sail surface and sunlight is controlled according to the suspension centripetal force, the suspension orbit requirement is met in real time, spiral suspension orbit operation is formed, revolution is performed along with the sun along with the earth, one-year regression is formed, and geocentric polar region suspension orbit operation of the next period continues. According to the invention, the comprehensive detection performance and observation efficiency of the polar spacecraft can be effectively improved.

Description

Technical Field

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

[0002] Traditional near-Earth artificial spacecraft are affected by the Earth's gravity, and their orbits are near-circular or large elliptical orbits around the Earth's center. The orbital characteristics are that the spacecraft orbital plane passes through the Earth's center, and through the periodic motion of the orbit, it conducts periodic interval observation and communication tasks on the ground. For the observation and communication tasks of the North and South Poles, polar orbit spacecraft or sun-synchronous orbit spacecraft with an orbital inclination of nearly 90 degrees are currently used to achieve short observation and communication time in the polar region per orbit. This is quite unfavorable for countries located in high-latitude areas. Therefore, Russia proposed the Molniya "Lightning" orbit, which is characterized by a special large elliptical orbit design, selecting a frozen orbit with an orbital inclination of 63.4°, offsetting the influence of the non-spherical gravitational perturbation term of the Earth, freezing the large elliptical orbit apses, and using the fact that the spacecraft's running speed near the apogee is much lower than the perigee speed, ensuring that each orbit has a longer transit time in the latitude area, especially over the polar regions, to achieve intermittent observation and communication tasks in the polar regions, each time for a longer time than the polar orbit. However, neither polar orbit, sun-synchronous orbit spacecraft nor Molniya orbit spacecraft can achieve uninterrupted, sustained and long-term continuous observation and communication tasks in the polar regions.

[0003] In recent years, in order to achieve uninterrupted, continuous and long-term stay of spacecraft over the polar regions, foreign research teams have used the huge sail surface of solar sails and the reflection of sunlight to provide a certain force to offset part of the gravity of the earth and the sun, so that its orbital plane no longer passes through the center of the earth, allowing the spacecraft to fly in circles over the polar regions, thus achieving a heliocentric polar suspension orbit at the Sun-Earth Lagrange L1 point. The heliocentric point here is because its orbit is far away from the earth, about 1.5 million kilometers, and is subject to the same gravitational effects of the sun and the earth. Although the heliocentric polar suspension spacecraft can meet the uninterrupted, continuous and long-term continuous observation and communication mission requirements of the polar regions, the distance of 1.5 million kilometers severely limits its application performance. Summary of the invention

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

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

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

[0007] Step S1: setting a graphene film sail for the geocentric polar levitation spacecraft, interacting the graphene film sail with the sun's rays, and calculating the levitation centripetal force;

[0008] Step S2: Setting a control system to control the angle between the graphene film sail and the sunlight according to the centripetal force of the suspension, so as to meet the suspension orbit requirements in real time, form a spiral suspension orbit, and follow the earth's revolution with the sun to form a one-year return and continue the next cycle of the geocentric polar suspension orbit.

[0009] Preferably, the step S1 comprises: generating light force by the interaction between the graphene film sail and the sun's rays, and forming a centripetal force for providing a suspended orbital motion with the gravity generated by the earth:

[0010]

[0011] The centripetal force of the suspension meets the orbital requirements of the suspension radius and suspension height of the set suspension orbit.

[0012] Preferably, the control system in step S2 controls the angle between the graphene film sail and the sunlight to ensure that the angle between the geocentric suspension orbit plane and the ecliptic plane meets the requirement of an ecliptic obliquity angle of 23.5°, and operates on a suspension orbit at an altitude of 50,000 kilometers from the Earth's polar regions.

[0013] Preferably, a variable emissivity film is pasted on the graphene film sail surface, and the graphene film sail surface is reused as a graphene film variable absorptivity. By adjusting the reflectivity change law and the absorptivity change law through a strategy, unequal large force couples are generated to form an attitude control torque for controlling the attitude pointing of the sail surface.

[0014] Preferably, the attitude and pointing of the sail are controlled 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 obliquity, and formulating a control strategy based on the angle difference through a control algorithm to act on the graphene film sail to make the angle difference 0, thereby ensuring that the angle between the geocentric suspension orbital plane and the ecliptic plane meets the ecliptic obliquity requirement of 23.5°.

[0015] Preferably, the angle between the geocentric suspension orbit plane and the ecliptic plane meets the requirement of 23.5° ecliptic obliquity at any time, and the normal of the geocentric suspension orbit plane is on an inverted cone surface with a semi-cone angle of 23.5° along the normal of the ecliptic plane. As time goes by, it rotates in the same direction and at the same rate as the earth's revolution.

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

[0017] Preferably, a thin-film solar cell array is attached to the graphene film sail surface to generate electrical energy to supply the energy needs of the spacecraft.

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

[0019] Module M1: Set up a graphene film sail for the Earth's center polar suspension spacecraft, interact with the sun's rays through the graphene film sail, and calculate the suspension centripetal force;

[0020] 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 the suspension, meet the suspension orbit requirements in real time, form a spiral suspension orbit, and follow the earth's revolution with the sun to form a one-year return and continue the next cycle of the geocentric polar suspension orbit.

[0021] Preferably, the module M1 comprises: generating light force through the interaction between the graphene film sail and the sun's rays, and forming a centripetal force for providing a suspended orbital operation with the gravity generated by the earth:

[0022]

[0023] The centripetal force of the suspension meets the orbital requirements of the suspension radius and suspension height of the set suspension orbit;

[0024] The control system in the module M2 controls the angle between the graphene film sail and the sunlight to ensure that the angle between the geocentric suspension orbit plane and the ecliptic plane meets the requirement of 23.5°, and operates on a suspension orbit at an altitude of 50,000 kilometers from the Earth's polar region;

[0025] The graphene film sail is pasted with a variable emissivity film, and the graphene film sail is reused as a graphene film with variable absorptivity. By adjusting the reflectivity change law and the absorptivity change law through a strategy, unequal large force couples are generated to form an attitude control torque, which is used to control the attitude pointing of the sail;

[0026] The attitude and direction of the control sail is controlled by measuring the angle between the entire plane of the graphene film sail and the sun's rays in real time, calculating the angle difference between the angle and the ecliptic angle, and formulating a control strategy based on the angle difference through a control algorithm to act on the graphene film sail so that the angle difference is 0, ensuring that the angle between the geocentric suspension orbital plane and the ecliptic plane meets the requirement of the ecliptic angle of 23.5°;

[0027] The angle between the geocentric suspension orbit plane and the ecliptic plane meets the requirement of an ecliptic obliquity angle of 23.5° at any time, and the normal of the geocentric suspension orbit plane is on an inverted cone surface with a semi-cone angle of 23.5° along the normal of the ecliptic plane, and rotates in the same direction and at the same rate as the earth's revolution as time passes;

[0028] The graphene film sail surface is multiplexed into a graphene antenna, which is used as a transmission and receiving antenna for transmitting data and information to the ground;

[0029] A thin-film solar cell array is attached to the graphene film sail surface to generate electrical energy 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 application efficiency of the present invention is higher: the suspension orbit altitude is far lower than 1.5 million kilometers, which is equivalent to the GEO satellite orbit altitude. The original GEO satellite remote sensing, communication, navigation and other payloads can be smoothly applied to the geocentric polar suspension spacecraft of the present invention; at the same time, the uninterrupted, continuous and long-term observation, communication and navigation of the polar regions, the lower suspension altitude, the higher resolution of earth observation, the lower signal attenuation and the faster signal transmission greatly improve the application efficiency;

[0032] 2. The present invention has more power: The power generated by the graphene film solar sail of the present invention is more sufficient than that generated by traditional polar suspension spacecraft. Compared with electric propulsion, it has the advantage of not requiring the consumption of working fluid, allowing it to stay over the polar regions uninterruptedly, continuously and for a long time, and revolve around the sun with the earth, forming a cyclic orbit with a designable inner circle period and an outer circle with the same revolution period as the earth.

[0033] Other beneficial effects of the present invention will be explained in the specific implementation manner through the introduction of specific technical features and technical solutions. Through the introduction of these technical features and technical solutions, those skilled in the art should be able to understand the beneficial technical effects brought about by the technical features and technical solutions. BRIEF DESCRIPTION OF THE DRAWINGS

[0034] Other features, objects and advantages of the present invention will become more apparent from the detailed description of non-limiting embodiments made with reference to the following drawings:

[0035] Figure 1 A schematic diagram of the relationship between the forces on the geocentric suspended spacecraft provided by the present invention and its spatial position with the sun and the earth within a one-year period;

[0036] Figure 2 This is a schematic diagram of the spatial position of the normal line of the suspension orbit in one year;

[0037] Figure 3 A schematic diagram of the forces acting on the geocentric suspended spacecraft of the present invention on the winter solstice;

[0038] Figure 4 This is a simulation diagram of the one-year orbit of the geocentric floating spacecraft in the present invention. DETAILED DESCRIPTION

[0039] The present invention is 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 are not intended to limit the present invention in any form. It should be noted that, for those of ordinary skill in the art, several changes and improvements can also be made without departing from the concept of the present invention. These all belong to the protection scope of the present invention.

[0040] The embodiment of the present invention provides a long-term residence method for a geocentric polar suspension spacecraft, so that the spacecraft has the ability to reside and suspend for a long time over the north and south poles of the earth, at an altitude of about 50,000 kilometers from the poles, greatly improving the comprehensive detection performance and observation efficiency of polar spacecraft. The present invention uses a graphene film as the sail surface of the geocentric polar suspension spacecraft, through which it interacts with sunlight. Compared with the traditional polyimide film solar sail surface, the graphene film sail surface used in the present invention can provide tens to hundreds of times the light force, so that the suspension height of the polar suspension orbit spacecraft can be further reduced to the order of 50,000 kilometers. Within this space range, the gravitational effect of the sun on the spacecraft is much smaller than the gravitational effect of the earth on the spacecraft. Therefore, the geocentric polar suspension spacecraft is mainly affected by the earth's gravity. The light force generated by the graphene film sail surface and the earth's gravity form a combined force, that is, a centripetal force that allows the spacecraft to continue to operate in a suspension orbit over the earth's poles.

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

[0042] Step S1: Setting a graphene film sail for the geocentric polar levitation spacecraft, and generating a light force through the interaction between the graphene film sail and the sun's rays, and forming a levitation centripetal force with the gravity generated by the earth to provide levitation orbit operation:

[0043]

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

[0045] Step S2: Setting a control system to control the angle between the graphene film sail and the sunlight according to the centripetal force of the suspension, so as to meet the suspension orbit requirements in real time, form a spiral suspension orbit, and follow the earth's revolution with the sun, completing the cycle from the winter solstice to the vernal equinox, the summer solstice, the autumnal equinox, and then back to the winter solstice, forming a one-year return, and continuing the next cycle of the geocentric polar suspension orbit.

[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 suspension orbit plane and the ecliptic plane meets the requirement of 23.5° ecliptic obliquity, thereby realizing operation on a suspension orbit at an altitude of about 50,000 kilometers from the Earth's polar regions.

[0047] Specifically, a variable emissivity film is pasted on the graphene film sail, and the graphene film sail is reused as a graphene film with variable absorptivity. By strategically adjusting the reflectivity change law and the absorptivity change law, unequal large force couples are generated to form an attitude control torque, which is used to control the attitude pointing of the sail.

[0048] Among them, the attitude and direction of the sail are controlled 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 formulating a control strategy based on the angle difference through a control algorithm to act on the graphene film sail so that the angle difference is 0, ensuring that the angle between the geocentric suspension orbital plane and the ecliptic plane meets the requirement of an ecliptic angle of 23.5°. The angle between the geocentric suspension orbital plane and the ecliptic plane meets the requirement of an ecliptic angle of 23.5° at any time. The normal of the geocentric suspension orbital plane is on an inverted cone with a semi-cone angle of 23.5° along the normal of the ecliptic plane. As time passes, it rotates in the same direction and at the same rate as the earth's revolution. Figure 2 shown.

[0049] The graphene film sail is multiplexed into a graphene antenna, which is used as a transmission and receiving antenna for data and information transmission to the ground.

[0050] A thin-film solar cell array is attached to the graphene film sail to generate electricity to supply the energy needs of the spacecraft.

[0051] Reference Figure 3As shown in the figure, on the winter solstice, the normal of the geocentric suspension orbit plane coincides with the earth's rotation axis. The angle between the sail and the sunlight is adjusted through the control algorithm, so that the resultant force of the light force on the spacecraft sail and the earth's gravity, that is, the centripetal force of suspension, meets the orbit requirements of the suspension radius ρ and the suspension height h of the suspension orbit. As time goes by, the spacecraft formulates and generates a control strategy through the control algorithm of the control system, continuously controls the angle between the sail and the sunlight, meets the suspension orbit requirements in real time, forms a spiral suspension orbit, and follows the earth's revolution with the sun, completes the journey from the winter solstice to the vernal equinox, summer solstice, autumnal equinox, and back to the winter solstice, forming a one-year return, and continues the next cycle of geocentric polar suspension orbit operation, as shown in the figure. Figure 1 and Figure 4 The orbit requirements of the suspension orbit suspension radius ρ and suspension height h 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] Among them, 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 surface and the orbital plane, ω is the angular velocity of the inner circle of suspension, and T is the inner circle period of suspension.

[0057] The present invention also provides a long-term residence system for a geocentric polar suspended spacecraft, which can be implemented by executing the process steps of the geocentric polar suspended spacecraft long-term residence method, that is, those skilled in the art can understand the geocentric polar suspended spacecraft long-term residence method as a preferred implementation of the geocentric polar suspended spacecraft long-term residence system. The system specifically includes:

[0058] Module M1: A graphene film sail is set up for the geocentric polar suspension spacecraft. The graphene film sail interacts with the sun's rays to generate light force, which, together with the gravity generated by the earth, forms a centripetal force to provide suspension orbit operation:

[0059]

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

[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 the suspension, meet the suspension orbit requirements in real time, form a spiral suspension orbit, and follow the earth's revolution with the sun, complete the journey from the winter solstice to the vernal equinox, summer solstice, autumnal equinox, and back to the winter solstice, forming a one-year return and continuing the next cycle of the geocentric polar suspension orbit.

[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 suspension orbit plane and the ecliptic plane meets the requirement of 23.5° ecliptic obliquity, thereby realizing operation on a suspension orbit at an altitude of about 50,000 kilometers from the Earth's polar regions.

[0063] Specifically, a variable emissivity film is pasted on the graphene film sail, and the graphene film sail is reused as a graphene film with variable absorptivity. By strategically adjusting the reflectivity change law and the absorptivity change law, unequal large force couples are generated to form an attitude control torque, which is used to control the attitude pointing of the sail.

[0064] Among them, the attitude and direction of the sail are controlled 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 formulating a control strategy based on the angle difference through a control algorithm to act on the graphene film sail so that the angle difference is 0, ensuring that the angle between the geocentric suspension orbital plane and the ecliptic plane meets the requirement of an ecliptic angle of 23.5°. The angle between the geocentric suspension orbital plane and the ecliptic plane meets the requirement of an ecliptic angle of 23.5° at any time. The normal of the geocentric suspension orbital plane is on an inverted cone with a semi-cone angle of 23.5° along the normal of the ecliptic plane. As time passes, it rotates in the same direction and at the same rate as the earth's revolution. Figure 2 shown.

[0065] The graphene film sail is multiplexed into a graphene antenna, which is used as a transmission and receiving antenna for data and information transmission to the ground.

[0066] A thin-film solar cell array is attached to the graphene film sail to generate electricity to supply the energy needs of the spacecraft.

[0067] Reference Figure 3As shown in the figure, on the winter solstice, the normal of the geocentric suspension orbit plane coincides with the earth's rotation axis. The angle between the sail and the sunlight is adjusted through the control algorithm, so that the resultant force of the light force on the spacecraft sail and the earth's gravity, that is, the centripetal force of suspension, meets the orbit requirements of the suspension radius ρ and the suspension height h of the suspension orbit. As time goes by, the spacecraft formulates and generates a control strategy through the control algorithm of the control system, continuously controls the angle between the sail and the sunlight, meets the suspension orbit requirements in real time, forms a spiral suspension orbit, and follows the earth's revolution with the sun, completes the journey from the winter solstice to the vernal equinox, summer solstice, and autumnal equinox, and returns to the winter solstice, forming a one-year return, and continues the next cycle of geocentric polar suspension orbit operation, as shown in the figure. Figure 1 and Figure 4 shown.

[0068] Next, the present invention will be described in more detail.

[0069] The present invention provides a method for long-term residence of geocentric polar suspended spacecraft, which has the ability to reside and suspend for a long time above the North and South Poles of the Earth, at an altitude of about 50,000 kilometers from the poles. It can be applied to high-resolution, high-efficiency, high-value polar observation, polar navigation, polar communication and other aerospace missions, which will effectively improve the comprehensive detection performance and observation efficiency of polar spacecraft.

[0070] The method of the present invention includes a graphene film sail, which reacts with the sun's rays to generate a light force, and forms a suspension centripetal force with the earth's gravity to provide a suspension orbit operation, and the suspension centripetal force needs to meet the orbit requirements of the suspension radius and suspension height of the suspension orbit. At the same time, a control strategy is formulated through the control system of the geocentric polar suspension spacecraft to control the angle between the graphene film sail and the sun's rays in real time, ensuring that the angle between the suspension orbit plane and the ecliptic plane meets the ecliptic obliquity angle of 23.5°, and realizes operation on a suspension orbit at an altitude of 50,000 kilometers from the earth's polar region. It can be applied to high-resolution, high-efficiency, high-value polar observation, polar navigation, polar communication and other aerospace missions, which will effectively improve the comprehensive detection performance and observation efficiency of polar spacecraft.

[0071] The geocentric polar suspension spacecraft includes a graphene film sail, a control system, and energy supply, communication, remote sensing, navigation and other payloads. The graphene film sail is prepared by a certain process method, and can interact with sunlight, laser, etc., to generate light force tens to hundreds of times that of traditional solar sails, which is the power source of the geocentric suspension orbit spacecraft without consuming working fluid; the control system implements attitude control of the spacecraft by means of, but not limited to, a variable reflectivity film, and adjusts the angle between the spacecraft sail and the sunlight in real time to ensure that the angle between the suspension orbit plane and the ecliptic plane meets the ecliptic obliquity angle of 23.5°; the energy supply is a flexible solar cell array attached to the film sail, which provides electrical energy supply for the entire geocentric polar suspension spacecraft; the communication, remote sensing, navigation and other payloads include but are not limited to earth observation remote sensing payloads, communication payloads, and navigation payloads that can be applied to GEO orbit satellites.

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

[0073] in, Figure 3 and Figure 4 In the figure, 1 is the sun; 2 is the earth; 21 is the earth's equator; 22 is the earth's polar region; 23 is the earth's rotation axis; 3 is the geocentric polar floating spacecraft; 31 is the graphene film sail of the geocentric polar floating spacecraft; 32 is the control system of the geocentric polar floating spacecraft.

[0074] The embodiment of the present invention provides a method and system for long-term residence of a geocentric polar suspended spacecraft, which generates light force through interaction with the sun's rays, and forms a suspension centripetal force with the earth's gravity to provide suspension orbit operation, and the suspension centripetal force meets the orbital requirements of the suspension radius and suspension height of the suspension orbit. At the same time, the control strategy is formulated by the control system of the geocentric polar suspended spacecraft to control the angle between the graphene film sail and the sun's rays in real time, ensuring that the angle between the suspension orbit plane and the ecliptic plane meets the ecliptic obliquity angle of 23.5°, and realizes operation on a suspension orbit at an altitude of about 50,000 kilometers from the earth's polar region. It can be applied to high-resolution, high-efficiency, high-value polar observation, polar navigation, polar communication and other aerospace missions, which will effectively improve the comprehensive detection performance and observation efficiency of polar spacecraft.

[0075] Those skilled in the art know that, in addition to realizing the system and its various devices, modules, and units provided by the present invention in a purely computer-readable program code, it is entirely possible to realize the same functions in the form of logic gates, switches, application-specific integrated circuits, programmable logic controllers, and embedded microcontrollers by logically programming the method steps. Therefore, the system and its various devices, modules, and units provided by the present invention can be considered as a hardware component, and the devices, modules, and units included therein for realizing various functions can also be regarded as structures within the hardware component; the devices, modules, and units for realizing various functions can also be regarded as both software modules for realizing the method and structures within the hardware component.

[0076] The above describes the specific embodiments of the present invention. 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. In the absence of conflict, the embodiments of the present application and the features in the embodiments can be combined with each other arbitrarily.

Claims

1. A method for long-term residence of a spacecraft suspended in the center of the earth and at the polar regions, characterized in that: include: Step S1: setting a graphene film sail for the geocentric polar levitation spacecraft, interacting the graphene film sail with the sun's rays, and calculating the levitation centripetal force; Step S2: Setting a control system to control the angle between the graphene film sail and the sunlight according to the centripetal force of the suspension, so as to meet the suspension orbit requirements in real time, form a spiral suspension orbit, and follow the earth's revolution with the sun to form a one-year return and continue the next cycle of the geocentric polar suspension orbit.

2. The long-term residence method of a geocentric polar suspended spacecraft according to claim 1, characterized in that: The step S1 includes: generating light force through the interaction between the graphene film sail and the sun's rays, and forming a centripetal force for providing a suspended orbital motion with the gravity generated by the earth: The centripetal force of the suspension meets the orbital requirements of the suspension radius and suspension height of the set suspension orbit.

3. The long-term residence method of a geocentric polar suspended spacecraft according to claim 1, characterized in that: The control system in step S2 controls the angle between the graphene film sail and the sunlight to ensure that the angle between the geocentric suspension orbit plane and the ecliptic plane meets the requirement of 23.5° ecliptic obliquity angle, and operates on a suspension orbit at an altitude of 50,000 kilometers from the Earth's polar region.

4. The long-term residence method of a geocentric polar suspended spacecraft according to claim 1, characterized in that: The graphene film sail is pasted with a variable emissivity film, and the graphene film sail is reused as a graphene film with variable absorptivity. By adjusting the reflectivity change law and the absorptivity change law through a strategy, unequal large force couples are generated to form an attitude control torque for controlling the attitude pointing of the sail.

5. The long-term residence method of a geocentric polar suspended spacecraft according to claim 4, characterized in that: The attitude and pointing direction of the control sail is controlled 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 formulating a control strategy based on the angle difference through a control algorithm, which acts on the graphene film sail to make the angle difference 0, thereby ensuring that the angle between the geocentric suspension orbital plane and the ecliptic plane meets the ecliptic angle requirement of 23.5°.

6. The long-term residence method of a geocentric polar suspended spacecraft according to claim 5, characterized in that: The angle between the geocentric suspension orbit plane and the ecliptic plane meets the requirement of 23.5° ecliptic obliquity at any time. The normal of the geocentric suspension orbit plane is on an inverted cone surface with a semi-cone angle of 23.5° along the normal of the ecliptic plane. As time goes by, it rotates in the same direction and at the same rate as the earth's revolution.

7. The long-term residence method of a geocentric polar suspended spacecraft according to claim 1, characterized in that: The graphene film sail surface is multiplexed into a graphene antenna, which is used as a transmission and receiving antenna for transmitting data and information to the ground.

8. The long-term residence method of a geocentric polar suspended spacecraft according to claim 1, characterized in that: A thin-film solar cell array is attached to the graphene film sail surface to generate electrical energy to supply the energy needs of the spacecraft.

9. A long-term residence system for geocentric polar suspended spacecraft, characterized in that: include: Module M1: Set up a graphene film sail for the Earth's center polar suspension spacecraft, interact with the sun's rays through the graphene film sail, and calculate the suspension centripetal force; 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 the suspension, meet the suspension orbit requirements in real time, form a spiral suspension orbit, and follow the earth's revolution with the sun to form a one-year return and continue the next cycle of the geocentric polar suspension orbit.

10. The long-term residence system of the geocentric polar suspended spacecraft according to claim 9, characterized in that: The module M1 includes: generating light force through the interaction between the graphene film sail and the sun's rays, and forming a centripetal force with the gravity generated by the earth to provide a suspended orbital operation: The centripetal force of the suspension meets the orbital requirements of the suspension radius and suspension height of the set suspension orbit; The control system in the module M2 controls the angle between the graphene film sail and the sunlight to ensure that the angle between the geocentric suspension orbit plane and the ecliptic plane meets the requirement of 23.5°, and operates on a suspension orbit at an altitude of 50,000 kilometers from the Earth's polar region; The graphene film sail is pasted with a variable emissivity film, and the graphene film sail is reused as a graphene film with variable absorptivity. By adjusting the reflectivity change law and the absorptivity change law through a strategy, unequal large force couples are generated to form an attitude control torque, which is used to control the attitude pointing of the sail; The attitude and direction of the control sail is controlled by measuring the angle between the entire plane of the graphene film sail and the sun's rays in real time, calculating the angle difference between the angle and the ecliptic angle, and formulating a control strategy based on the angle difference through a control algorithm to act on the graphene film sail so that the angle difference is 0, ensuring that the angle between the geocentric suspension orbital plane and the ecliptic plane meets the requirement of the ecliptic angle of 23.5°; The angle between the geocentric suspension orbit plane and the ecliptic plane meets the requirement of an ecliptic obliquity angle of 23.5° at any time, and the normal of the geocentric suspension orbit plane is on an inverted cone surface with a semi-cone angle of 23.5° along the normal of the ecliptic plane, and rotates in the same direction and at the same rate as the earth's revolution as time passes; The graphene film sail surface is multiplexed into a graphene antenna, which is used as a transmission and receiving antenna for transmitting data and information to the ground; A thin-film solar cell array is attached to the graphene film sail surface to generate electrical energy to supply the energy needs of the spacecraft.

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