A spaceborne sunlight reflection device and a spaceborne sunlight reflection control method

Abstract

The application provides a satellite-borne sunlight reflection device and a satellite-borne sunlight reflection control method, and the satellite-borne sunlight reflection device comprises at least one on-satellite reflection plate and a satellite main body; the satellite main body is used for adjusting an attitude reflection angle between the on-satellite reflection plate and parallel sunlight; the on-satellite reflection plate is connected with the satellite main body, and in operation, a reflection surface faces a direction of irradiation of the parallel sunlight and is used for reflecting the parallel sunlight to a dark area on the earth surface; the satellite main body adjusts the attitude reflection angle of the on-satellite reflection plate by adjusting an attitude, and adjusts a ground reflection light intensity. The satellite-borne sunlight reflection device can adjust sunlight reflection to a shadow position on the earth, so as to accurately control the reflectivity, and the reflectivity and reflection position of a reflection area can be accurately controlled, and the influence of the satellite-borne sunlight reflection on other areas is reduced.

Description

Technical Field

[0001] This invention relates to the field of satellite control technology, and in particular to a spaceborne solar reflector and a spaceborne solar reflector control method. Background Technology

[0002] Satellites reflect sunlight to provide nighttime illumination. With their zero-infrastructure deployment, full-area coverage, and environmentally friendly nature, they are of great significance to human life, especially suitable for areas such as mountains and deserts where traditional lighting is difficult to reach. In emergency rescue operations, during disasters such as mountain earthquakes and desert fires, satellites can quickly and accurately cover the affected area without the need to transport or set up equipment, providing a stable light source for rescue, search and rescue, and material transfer. After the rescue, no equipment is left behind, avoiding ecological damage and waste pollution, solving the pain points of traditional emergency lighting equipment being difficult to deploy and prone to leaving residue. In field scenarios, activities such as mountain scientific expeditions and desert exploration do not require carrying bulky generators and battery packs. Satellites continuously provide illumination, reducing the burden on equipment, adapting to complex terrain, and producing zero pollution and no waste throughout the process, meeting the needs of field ecological protection. Regarding highways and remote roads, laying streetlights in mountainous and desert sections is costly and difficult to maintain. Satellites can provide full-range illumination without blind spots, requiring no infrastructure construction. Long-term use does not involve equipment aging or abandonment issues, improving driving safety while being energy-efficient and environmentally friendly. In addition, its flexible and adjustable coverage and brightness can be adapted to various scenarios as needed, providing green and efficient new support for nighttime production, life and public safety in remote areas.

[0003] However, because the area covered by its reflected light beam is predetermined and cannot be adjusted, it obscures the real night sky, making astronomical observation virtually impossible and causing irreversible damage to astronomical research. Furthermore, these bright spots can injure the eyes of stargazers and even interfere with pilots' vision, increasing flight risks. Simultaneously, light pollution can alter animal behavior patterns, disrupt plant growth cycles, and even affect human sleep quality, thus causing serious disruption to production, daily life, and scientific research.

[0004] Therefore, the proposal and implementation of this invention will provide a better solution for the above-mentioned scenarios. Summary of the Invention

[0005] In view of the shortcomings of the prior art, the purpose of this invention is to provide a spaceborne solar reflector and a spaceborne solar reflector control method to solve the problem that existing satellite solar reflector schemes cannot freely adjust the coverage range of the reflected beam.

[0006] The technical solution of the present invention is as follows: This invention provides a spaceborne solar reflector, comprising: at least one onboard reflector and a satellite body; The satellite body is set on the satellite orbit and moves along the direction of the satellite orbit to detect the direction of parallel sunlight and adjust the attitude reflection angle between the on-board reflector and the parallel sunlight; The on-board reflector is connected to the satellite body and is perpendicular to the satellite orbit direction. The on-board reflector includes a reflective surface and a backlight plate, and the reflective surface is disposed on the upper surface of the backlight plate. During operation, the backlight panel is located on the side of the on-board reflector away from the parallel sunlight and the Earth's surface; the reflective surface is located on the side of the on-board reflector closer to the parallel sunlight and the Earth's surface, and faces the direction of the parallel sunlight, to reflect the parallel sunlight to the dark areas of the Earth's surface; the satellite body adjusts the attitude and reflection angle of the on-board reflector by adjusting its attitude, and adjusts the intensity of the reflected light from the ground.

[0007] In a further embodiment of the present invention, the on-board reflector is connected to the satellite body via a servo motor; when the servo motor rotates, it drives the on-board reflector to rotate along the servo motor's axis of rotation, thereby adjusting the deflection angle between the on-board reflector and parallel sunlight.

[0008] In a further embodiment of the present invention, the reflective surface of the on-board reflector comprises: a supporting substrate, a reflective layer, an electrically controlled transmission layer, an adhesive layer, and a quartz protective layer; wherein, The supporting substrate is disposed above the backlight plate of the on-board reflector; The reflective layer is disposed above the supporting substrate and is used to reflect incident parallel sunlight. The electrically controlled transmission layer is disposed above the reflective layer and is electrically connected to the voltage control circuit, used to adjust the reflectivity of the on-board reflector according to the input voltage; The quartz protective layer is located above the electrically controlled transmission layer and is used to protect the reflective surface structure; The adhesive layers are respectively disposed between the supporting substrate and the backlight panel, the reflective layer and the supporting substrate, the electrically controlled transmission layer and the reflective layer, and the quartz protective layer and the electrically controlled transmission layer, for bonding and fixing the supporting substrate and the backlight panel, the reflective layer and the supporting substrate, the electrically controlled transmission layer and the reflective layer, and the quartz protective layer and the electrically controlled transmission layer.

[0009] In a further embodiment of the present invention, the reflective surface includes a plurality of adjustable reflective units; the adjustable reflective units are arranged in an array on the upper surface of the backlight panel; each adjustable reflective unit includes: a light-receiving reflective plate, a plurality of support columns, and a base; wherein, The edge of the light-receiving reflector is connected to the top of each of the supporting columns with full freedom of movement; The bottom end of the support column is connected to the upper surface of the base with full freedom of movement. The length of the support column is adjustable to adjust the shape and angle of the light-receiving reflector. The base is equipped with a control circuit for controlling the length of the support column, and the lower surface of the base is disposed on the upper surface of the backlight panel.

[0010] In a further embodiment of the present invention, the support column is provided with a telescopic adjustment structure, which is one of a heating element, a piezoelectric motor, or a micro motor.

[0011] In a further embodiment of the present invention, a satellite attitude control component is provided inside the satellite body, which is used to adjust the attitude reflection angle between the on-board reflector and parallel sunlight by adjusting the attitude of the satellite body.

[0012] A further provision of the present invention includes a heat-conducting layer disposed on the upper surface of the backlight panel and in contact with the lower surface of the base of each adjustable reflective unit, for absorbing and conducting heat on the adjustable reflective unit.

[0013] In a further embodiment of the present invention, at least one light intensity sensor is disposed on the upper surface of the reflective surface, the light intensity sensor being used to detect the light intensity of parallel sunlight.

[0014] Based on the same inventive concept, this invention provides a spaceborne solar radiation reflection control method. The aforementioned spaceborne solar radiation reflection device is used to implement the spaceborne solar radiation reflection control method, and the steps include: The satellite body senses the received light intensity on the onboard reflector; The satellite body calculates the initial light intensity based on the received light intensity; The satellite body adjusts its own attitude to adjust the attitude and reflection angle of the onboard reflector, and then adjusts the area of ​​the ground reflection region and the intensity of the ground reflected light according to the initial light intensity.

[0015] A further provision of the present invention includes a receiving station located in the ground reflection area, the receiving station being used to detect the actual ground light intensity over the area of ​​the ground reflection area. Following the step of adjusting the area of ​​the ground reflection area and the ground reflected light intensity by adjusting the onboard reflector and the satellite body, the invention further includes: The light intensity difference is obtained based on the ground reflected light intensity and the actual ground light intensity, and the attitude reflection angle and deflection angle are adjusted negatively based on the light intensity difference.

[0016] This invention provides a spaceborne solar reflector and a spaceborne solar reflector control method. The spaceborne solar reflector includes: at least one onboard reflector and a satellite body; the satellite body is positioned in a satellite orbit and moves along the orbital direction to detect the direction of parallel sunlight and adjust the attitude reflection angle between the onboard reflector and the parallel sunlight; the onboard reflector is connected to the satellite body and is perpendicular to the satellite orbital direction; the onboard reflector includes a reflective surface and a backlight plate, the reflective surface being disposed on the upper surface of the backlight plate; during operation, the backlight plate is located on the side of the onboard reflector away from the parallel sunlight and the Earth's surface; the reflective surface is located on the side of the onboard reflector closer to the parallel sunlight and the Earth's surface, facing the direction of the parallel sunlight, and is used to reflect the parallel sunlight to the dark areas of the Earth's surface; the satellite body adjusts the attitude reflection angle of the onboard reflector and adjusts the intensity of ground-reflected light by adjusting its attitude. This invention uses a spaceborne solar reflector to adjust the reflection of sunlight to the Earth's shadow position, thereby precisely controlling the reflectivity. This allows for precise control of the reflectivity and reflection position of the reflective area, reducing the impact of spaceborne solar reflection on other areas. Attached Figure Description

[0017] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on the structures shown in these drawings without creative effort.

[0018] Figure 1 This is a schematic diagram of the structure of the spaceborne solar reflector in this invention.

[0019] Figure 2 This is a schematic diagram illustrating the working principle of the spaceborne solar reflector in this invention.

[0020] Figure 3 This is a schematic diagram of the adjustable reflection unit in this invention.

[0021] Figure 4 This is a schematic diagram of the multi-layer structure of the reflective surface in this invention.

[0022] Figure 5 This is a schematic diagram of the adjustable reflective units arranged in an array on the reflective surface in this invention.

[0023] Figure 6 yes Figure 5 Enlarged schematic diagram of the cross-section of the support column at position A.

[0024] Figure 7This is a schematic diagram of the planar state of the light-receiving reflector of the adjustable reflection unit in this invention.

[0025] Figure 8 This is a schematic diagram of the convex surface state of the light-receiving reflector of the adjustable reflective unit in this invention.

[0026] Figure 9 This is a schematic diagram of the concave surface state of the light-receiving reflector of the adjustable reflective unit in this invention.

[0027] Figure 10 This is a schematic diagram of the structure in which the reflective surface of the adjustable reflective unit in this invention is in a concave state.

[0028] Figure 11 This is a schematic diagram of the structure in which the reflective surface of the adjustable reflective unit in this invention is in a convex state.

[0029] The markings in the attached diagram are as follows: 1. Onboard reflector; 11. Reflective surface; 1111. Support substrate; 1112. Reflective layer; 1113. Electrically controlled transmission layer; 1114. Adhesive layer; 1115. Quartz protective layer; 110. Adjustable reflection unit; 111. Light-receiving reflector; 112. Support column; 1121. Heating element; 113. Base; 12. Backlight panel; 2. Satellite body; 3. Servo motor. Detailed Implementation

[0030] This invention provides a spaceborne solar reflector and a spaceborne solar reflector control method. To make the objectives, technical solutions, and effects of this invention clearer and more explicit, the invention will be further described in detail below with reference to the accompanying drawings and examples. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.

[0031] In the implementation methods and claims, unless otherwise specified in the text, the terms "a," "an," "the," and "the" may also include plural forms. If the embodiments of the present invention involve descriptions of "first," "second," etc., such descriptions are for descriptive purposes only and should not be construed as indicating or implying their relative importance or implicitly specifying the number of indicated technical features. Therefore, a feature defined with "first" or "second" may explicitly or implicitly include at least one of those features.

[0032] It should be further understood that the term "comprising" as used in this specification means the presence of the stated features, integers, steps, operations, elements, and / or components, but does not exclude the presence or addition of one or more other features, integers, steps, operations, elements, components, and / or groups thereof. It should be understood that when we say an element is "connected" or "coupled" to another element, it can be directly connected or coupled to the other element, or there may be intermediate elements. Furthermore, "connected" or "coupled" as used herein can include wireless connections or wireless coupling. The term "and / or" as used herein includes all or any unit and all combinations of one or more associated listed items.

[0033] It will be understood by those skilled in the art that, unless otherwise defined, all terms used herein (including technical and scientific terms) have the same meaning as commonly understood by one of ordinary skill in the art to which this invention pertains. It should also be understood that terms such as those defined in general dictionaries should be understood to have the same meaning as in the context of the prior art, and should not be interpreted in an idealized or overly formal sense unless specifically defined as herein.

[0034] Furthermore, the technical solutions of the various embodiments can be combined with each other, but only if they are feasible for those skilled in the art. If the combination of technical solutions is contradictory or cannot be implemented, it should be considered that such combination of technical solutions does not exist and is not within the scope of protection claimed by this invention.

[0035] In 1988, Russia successfully launched a 65-foot-tall mirror into space, reflecting a 5-kilometer-wide beam of light across Europe. In 2017, a Norwegian erected a large, rotating mirror on a mountain in Rjukan to alleviate seasonal affective disorder (SAD) caused by lack of sunlight in high-latitude regions during winter. In 2018, the Tianfu System Science Research Association proposed the concept of an "artificial moon." An American startup proposed a service to bring sunlight into the night using giant mirrors on satellites; the team has already conducted related experiments on hot air balloons, initially demonstrating feasibility. The inventors' research revealed that existing technologies that illuminate dark areas by reflecting sunlight through mirrors cannot precisely adjust the angle and range of the reflected sunlight beam. When it streaks across the night sky, it often illuminates areas other than the target region. For example, when a beam of light reflected from a satellite sweeps across a telescope, the bright trail of sunlight reflected across the telescope's field of view contaminates long-exposure images. For modern observatories that rely on extremely low light levels to detect distant celestial objects, any additional light source reduces the instrument's detection limit, significantly interfering with ground-based astronomical observations. Meanwhile, artificial light at night suppresses melatonin production, thus affecting sleep regulation and impacting the immune system and physiological health. Light pollution also causes nocturnal species to alter their activity times, migration routes, and foraging strategies, thereby weakening individual adaptability and changing ecosystem structure. Nocturnal migratory birds are particularly sensitive to artificial light. Billions of birds fly across continents at night each year, relying on starlight and geomagnetic navigation. Urban lights have been proven to disorient migratory birds, leading to collisions with buildings and death. While orbital mirrors are not as concentrated as ground lighting, they can increase nighttime brightness over vast areas, potentially causing directional interference for high-altitude migratory species.

[0036] To address the technical problems existing in the current technology, please refer to the following: Figure 1 and Figure 2 This invention provides a spaceborne solar reflector, comprising: at least one onboard reflector 1 and a satellite body 2; the satellite body 2 is disposed on a satellite orbit and moves along the satellite orbit direction to detect the direction of parallel sunlight and adjust the attitude reflection angle between the onboard reflector 1 and the parallel sunlight; the onboard reflector 1 is connected to the satellite body 2 and is perpendicular to the satellite orbit direction, the onboard reflector 1 includes a reflective surface 11 and a backlight plate 12, the reflective surface 11 is disposed on the upper surface of the backlight plate 12; during operation, the backlight plate 12 is located on the side of the onboard reflector 1 away from the parallel sunlight and the Earth's surface; the reflective surface 11 is located on the side of the onboard reflector 1 closer to the parallel sunlight and the Earth's surface, facing the direction of the parallel sunlight, and is used to reflect the parallel sunlight to the dark areas of the Earth's surface; the satellite body 2 adjusts the attitude reflection angle of the onboard reflector 1 by adjusting its attitude and adjusts the intensity of ground reflected light.

[0037] Specifically, the onboard reflector 1 and the satellite body 2 can be fixedly connected or rotatably connected to reduce the satellite size during rocket launch, provide better structural support and protection, and prevent damage to the satellite in the launch dynamic environment. Specifically, the satellite body 2 can be equipped with various components to ensure the basic operational status of the satellite. For example, the satellite body 2 internally houses a satellite attitude control component, used to adjust the attitude reflection angle between the onboard reflector 1 and parallel sunlight by adjusting the attitude of the satellite body 2. The satellite attitude control component can be any existing component for adjusting satellite attitude. For example, it can include at least one or more of attitude detection and attitude adjustment components such as a laser gyroscope, magnetometer, sun sensor, star sensor, and magnetic torque meter. For example, the satellite body 2 can determine the direction of parallel sunlight using a sun sensor or other components. Since the direction of the onboard reflector 1 is known, the attitude reflection angle between the onboard reflector 1 and parallel sunlight can be obtained, thereby revealing the incident angle and reflection angle.

[0038] A spaceborne solar reflector is positioned in a satellite orbit, which can be a Low Earth Orbit (LEO), a Middle Earth Orbit (MEO), or a Geostationary Transfer Orbit (GEO). For example, this invention uses a low Earth Orbit satellite, operating at an altitude of approximately 300 to 2000 kilometers above the Earth's surface. At this altitude, sunlight can be considered parallel; a portion directly illuminates the Earth, representing daytime, while the portion not directly illuminated is considered nighttime. By deploying a satellite in this orbit, with the satellite itself or a portion serving as the spaceborne solar reflector, and by attaching a reflector to its surface and adjusting its angle, sunlight can be reflected into the Earth's nighttime region, thus adjusting the intensity and area of ​​the reflected light. The spaceborne solar reflector operates in low Earth orbit. The reflective surface 11 of the onboard reflector 1 continuously faces the side parallel to sunlight. This reflective surface 11 has a light-reflecting function and is used to reflect parallel sunlight to the Earth's nighttime areas. When the spaceborne solar reflector moves to a dark area in the nighttime region that needs to be illuminated, the satellite body 2 adjusts its attitude according to its relative position to the dark area, thereby adjusting the attitude reflection angle to track the light beam reflected by the onboard reflector 1 and the dark area on the ground. For example, for ease of explanation, the attitude reflection angle, referring to the satellite's body coordinate system, can include a roll angle and / or a yaw angle, meaning it can be adjusted by the attitude adjustment components causing the satellite body 2 to rotate along the roll axis and yaw axis, thereby adjusting the intensity of the ground-reflected light in the dark area. The ground reflection area is S. 地 Light intensity L 地 The light flux received by the satellite L 星 Reflective area S 形 The attitude reflection angle α caused by the satellite's attitude is related to the attenuation loss rate during the process. Assuming the attenuation loss rate is K and the ground area light intensity is L... 地 for:

[0039] Therefore, the spaceborne solar reflector can adjust the illuminated dark area and the corresponding ground reflected light intensity by adjusting the attitude reflection angle α.

[0040] Furthermore, such as Figure 2As shown, the on-board reflector 1 is connected to the satellite body 2 via a servo motor 3. When the servo motor 3 rotates, it drives the on-board reflector 1 to rotate along the servo motor 3's rotation axis, thereby adjusting the deflection angle between the on-board reflector 1 and the parallel sunlight. Specifically, the satellite attitude emission angle α is the assumed angle between the reflecting surface and the plane parallel to the sunlight. In this invention, this can be achieved by adding a servo motor 3 or similar angle adjustment device, or by adjusting the satellite attitude so that the reflecting mirror and the plane parallel to the sunlight generate a deflection angle β perpendicular to the plane containing the attitude reflection angle α. Preferably, this is achieved through the servo motor 3. The number of servo motors 3 is determined by the number of on-board reflectors 1. The rotation axis of the servo motor 3 coincides with the pitch axis of the satellite body 2, meaning that when the servo motor 3 rotates, it can drive the on-board reflector 1 to rotate along the pitch axis, thereby adjusting the deflection angle between the on-board reflector 1 and the parallel sunlight. It should be noted that the deflection angle is perpendicular to the attitude reflection angle of the satellite body 2 mentioned above. Therefore, by adding an angle adjustment device such as a servo motor 3, an angle is created between the onboard reflector 1 and the parallel sunlight. This angle is the deflection angle β. Regarding the deflection angle β:

[0041] Therefore, the onboard solar reflector can be adjusted by rotating the onboard reflector 1 via the servo motor 3, thereby regulating the intensity of reflected light from the ground. The satellite body 2 can also be equipped with other operational functional components, such as those used for remote sensing. When performing remote sensing, the satellite body 2 changes its attitude and tracks the ground; simultaneously, the satellite body 2 drives the servo motor 3 to rotate, ensuring that the onboard reflector 1 provides supplemental lighting to dark areas, making it easier for the satellite to perform other operations.

[0042] In some preferred embodiments, please refer to Figure 4The reflective surface 11 of the on-board reflector 1 includes: a supporting substrate 1111, a reflective layer 1112, an electrically controlled transmission layer 1113, an adhesive layer 1114, and a quartz protective layer 1115; wherein, the supporting substrate 1111 is disposed above the backlight plate 12 of the on-board reflector 1; the reflective layer 1112 is disposed above the supporting substrate 1111 and is used to reflect incident parallel sunlight; the electrically controlled transmission layer 1113 is disposed above the reflective layer 1112 and is electrically connected to a voltage control circuit for adjusting the reflectivity of the on-board reflector 1 according to the input voltage; A quartz protective layer 1115 is located above the electrically controlled transmission layer 1113 and is used to protect the reflective surface 11 structure. The adhesive layer 1114 is respectively disposed between the supporting substrate 1111 and the backlight panel 12, the reflective layer 1112 and the supporting substrate 1111, the electrically controlled transmission layer 1113 and the reflective layer 1112, and the quartz protective layer 1115 and the electrically controlled transmission layer, and is used to bond and fix the supporting substrate 1111 and the backlight panel 12, the reflective layer 1112 and the supporting substrate 1111, the electrically controlled transmission layer 1113 and the reflective layer 1112, and the quartz protective layer 1115 and the electrically controlled transmission layer 1113.

[0043] The supporting substrate 1111 can be made of materials such as aluminum alloy, silicon, or carbon fiber. It can be planar, or it can be convex or concave depending on the requirements. Based on preliminary calculations of the reflection scenario and intensity, a convex design is preferred, making the reflective surface 11 convex in shape. The supporting substrate 1111 can also be made of elastic or deformable materials, allowing the curvature of the reflector on the satellite to be changed by applying external force. By default, the onboard reflector 1 can be a convex mirror, thereby increasing the reflection area and further expanding the reflection range to illuminate a larger dark area. In some preferred embodiments of the invention, heat-conducting and heat-dissipating structures, such as silver, copper, gold, or aluminum layers, can be added to the supporting substrate 1111 to improve the overall performance of the reflective panel in space. The supporting substrate 1111 supports the upper-level structures. The reflective layer 1112 can be made of any material and is mainly used to reflect parallel sunlight. The film and surface coating adopt a thin sheet structure with a certain degree of flexibility, which can change accordingly with the shape of the supporting substrate 1111. For example, the reflective layer 1112 can be implemented using electroplated mercury or by surface bonding of a high-reflectivity material, primarily for reflecting parallel sunlight. An electrically controlled transmission layer 1113 is added to the surface of the reflective layer 1112. This layer can employ electrically controlled nano-silver, electrically controlled semi-transparent liquid crystal, or other electrically controlled methods. By applying an electric field to control the arrangement of molecules in the structure, the light transmittance is altered, achieving a switch between transparent and frosted surfaces. For example, using an electrically controlled nano-silver coating: when energized, the entire electrically controlled transmission layer 1113 is translucent, allowing the entire reflective panel to reflect sunlight. When de-energized, the nano-silver is opaque, and the entire reflective panel no longer reflects sunlight. The transmittance of this coating layer is related to the control voltage. By changing the magnitude and presence of the control voltage, the transmittance of the entire coating can be adjusted, thereby controlling the reflectivity of the entire reflective panel and enabling the on / off operation of the onboard reflector 1.

[0044] In some preferred embodiments, please refer to the following: Figure 1 , Figure 3 , Figure 5The reflective surface 11 includes a plurality of adjustable reflective units 110; the adjustable reflective units 110 are arranged in an array on the upper surface of the backlight panel 12; each adjustable reflective unit 110 includes: a light-receiving reflective plate 111, a plurality of support columns 112, and a base 113; wherein, the edge of the light-receiving reflective plate 111 is connected to the top of each support column 112 with full freedom; the bottom end of the support column 112 is connected to the upper surface of the base 113 with full freedom; the length of the support column 112 is adjustable to adjust the shape and angle of the light-receiving reflective plate 111; the base 113 is provided with a control circuit for controlling the length of the support column 112; the lower surface of the base 113 is disposed on the upper surface of the backlight panel 12.

[0045] Please refer to the following: Figure 1 , Figure 3 , Figure 5 as well as Figures 7 to 11The reflective surface 11 can be divided into several adjustable reflective units 110. The light-receiving reflective surfaces of each adjustable reflective unit 110 are adjacent to each other, and can be considered as a complete light-receiving reflector 111 macroscopically. The light-receiving reflectors 111 of each adjustable reflective unit 110 can have the same or different shapes, as long as they can achieve a tessellation pattern. For example, the adjustable reflective units 110 can be light-receiving reflectors 111 that can achieve a regular polygon tessellation pattern, such as hexagonal light-receiving reflectors 111, or other geometric shapes such as rectangles, triangles, and rhombuses. Depending on the orbital calculation and reflection requirements, as well as the satellite's carrying capacity, a satellite can carry one or more complete adjustable reflective units 110, which are arranged in an array so that the light-receiving reflectors 111 of each adjustable reflective unit 110 are spliced ​​together to form a complete reflective surface 11. For each adjustable reflective unit 110, the edge of its light-receiving reflector 111 is connected to the top of a support column 112, and the bottom of each support column 112 is connected to a base 113. Preferably, the light-receiving reflector 111 can be connected to three or more support columns 112, that is, the back of the light-receiving reflector 111 of each adjustable reflective unit 110 is supported by three or more support columns 112, and the support columns 112 are evenly distributed to make the load on each support column 112 as equal as possible. For example, when three support columns 112 are used to support a hexagonal light-receiving reflector 111, the angle between the projections of each support column 112 on the light-receiving reflector 111 is 120°. Each support column 112 and its base 113 are provided with independent power supply and control circuits, so that the deformation of each support column 112 can be adjusted. The length of the support column 112 can be adjusted by heating the support column 112 and / or by installing a motor on the support column 112. Preferably, the support column 112 is provided with a telescopic adjustment structure, which is one of a heating element, a piezoelectric motor, or a micro motor. Specifically, taking a heating element as an example, the adjustment method of the support column will be explained. Figure 6 , Figure 8 and Figure 9As shown, the support column 112 is a metal support column, and a heating element 1121 is provided on the outer surface of the support column 112. The length of the support column 112 increases when the heating element 1121 heats up, which is used to adjust the angle of the light-receiving reflector 111 of each adjustable reflector unit 110 and the overall degree of convergence of reflected light. This applies external force and adjusts the curvature of each light-receiving reflector 111, causing the reflected light from different light-receiving reflectors 111 to be superimposed on a designated area of ​​the Earth's surface, thus strengthening or weakening the brightness at that specific location. It should be noted that the curvature of the light-receiving reflector 111 on each adjustable reflector unit 110 can be the same or different. For example, at the same time, different adjustable reflector units 110 of a satellite reflector 1 can be set to concave, planar, and convex surfaces, respectively, and rotate at different angles. By varying the deformation of the support column 112, the reflection angle of each light-receiving reflector 111 can be determined. Thus, as a whole, different light-receiving reflectors 111 of a single satellite reflector 1 can independently control multiple reflection positions. When transmitting to Earth, the angle of each adjustable reflective unit 110 can be independently adjusted, ultimately resulting in different angles and areas of reflected light received by the Earth's surface. Furthermore, the light-receiving reflector 111 can also be a reflective surface 11 composed of a support substrate 1111, a reflective layer 1112, an electrically controlled transmission layer 1113, an adhesive layer 1114, and a quartz protective layer 1115, thereby simultaneously possessing reflectivity adjustment and reflection switch control functions, which will not be elaborated further here.

[0046] For example, more support columns 112 can be selected. Since any three non-collinear points in three-dimensional space can uniquely determine a plane, when four or more support columns 112 are used, the curvature of the reflective surface 11 can be adjusted by adjusting the length of one of the support columns 112, allowing the light-receiving reflector 111 to be adjusted between convex, planar, and concave surfaces. Thus, while adjusting the angle of the adjustable reflective unit 110, its curvature can also be adjusted. In some preferred embodiments, a force sensor (not shown in the figure) can also be added to each reflective surface. This sensor can be any flexible or rigid sensor to collect the deformation of different support columns 112 at the bottom of each light-receiving reflective surface. Based on this, the deformation of this light-receiving reflective surface relative to the reflective surface of the entire on-board reflector 1 can be calculated, and the relative tilt angle can be obtained.

[0047] Furthermore, the onboard reflector 1 of the spaceborne solar reflector also includes a heat-conducting layer (not shown in the figure). This heat-conducting layer is disposed on the upper surface of the backlight plate 12 and contacts the lower surface of the base 113 of each adjustable reflector unit 110, for absorbing and conducting heat from the adjustable reflector unit 110. Preferably, the heat-conducting layer is made of aluminum and is located on the lower surface of the reflective surface 11. When the reflective surface 11 uses several adjustable reflector units 110, the heat-conducting layer is located on the lower surface of its base 113, for absorbing heat emitted from the internal control circuit of the base 113 and releasing excess solar energy using thermal radiation and other technical principles. Correspondingly, one or more temperature sensors can also be added to the reflector to prevent the spacecraft from overheating and causing equipment malfunctions. At least one light intensity sensor is disposed on the upper surface of the reflective surface 11, for detecting the intensity of parallel sunlight. Thus, by sensing the light intensity obtained by the spacecraft reflector in real time, the initial light intensity can be calculated. This function can also be achieved through attitude calculation, which calculates the angle between the spacecraft's reflector and the parallel sunlight.

[0048] Based on the same inventive concept, this invention provides a method for controlling spaceborne solar radiation reflection, comprising the following steps: S100, the satellite body senses the received light intensity on the onboard reflector; S200: The satellite body calculates the initial light intensity based on the received light intensity; S300: The satellite body adjusts its own attitude to adjust the attitude and reflection angle of the onboard reflector, and then adjusts the ground reflection area and ground reflection intensity according to the initial light intensity.

[0049] The specific implementation details are as described in the above-mentioned specific embodiments of the spaceborne solar reflector, and will not be repeated here.

[0050] Furthermore, a receiving station is set up in the ground reflection area. The receiving station is used to detect the actual ground light intensity over the area of ​​the ground reflection area. After the step of adjusting the area of ​​the ground reflection area and the ground reflected light intensity by adjusting the on-board reflector and the satellite body, the method further includes: S400. Based on the ground reflected light intensity and the actual ground light intensity, obtain the light intensity difference, and adjust the attitude reflection angle and deflection angle with negative feedback based on the light intensity difference.

[0051] Specifically, in this preferred embodiment, a receiving station can be set up in the reflection area on the ground. This receiving station can communicate with the spaceborne solar reflector and receive the reflected light intensity of the spaceborne solar reflector at different locations, times, and adjustment methods. It then uploads the relevant information to the spaceborne solar reflector, allowing it to calibrate based on real-time data from the ground and adjust specific implementation parameters accordingly. For example, this negative feedback process can calculate the light intensity difference as an error value by comparing the actual light intensity monitored by the ground sensor network with the preset theoretical ground reflected light intensity in real time. This error value is then input into a pre-determined precision control algorithm based on spatial geometry, optics, and atmospheric transmission models to obtain a feedback adjustment command. This command adjusts the reflector's attitude and reflection angle, finely adjusting the mirror deflection angle and curvature to optimize the beam intensity, ensuring the beam covers the target area, thus forming a closed-loop negative feedback control circuit. Its core principle is to continuously apply an adjustment amount opposite to the direction of the error, driving the actual light intensity to automatically stabilize at a preset value. This allows the system to dynamically compensate for the impact of orbital and attitude deviations, atmospheric disturbances, and other interferences on the reflection process during operation, achieving high precision and long-term stability in light output. Simultaneously, this invention, through a negative feedback loop, enables the spaceborne solar reflector to adapt to environmental changes and gradual changes in equipment performance, improving light resource utilization efficiency, reducing energy consumption and light pollution, while simultaneously enhancing the accuracy, reliability, and adaptability of the adjustment of reflection position and reflected light intensity during the process.

[0052] In summary, the present invention provides a spaceborne solar reflector and a spaceborne solar reflector control method, the beneficial effects of which include: The spacecraft's reflector can be adjusted in various ways, such as attitude adjustment, servo adjustment, switch adjustment, light intensity adjustment, and convergence adjustment, according to user needs, orbital altitude, weather conditions, etc., thereby achieving light intensity control in a designated area on the Earth's surface.

[0053] By using a spaceborne solar reflector, sunlight can be reflected to the Earth's shadow, thereby precisely controlling the reflectivity. This allows for precise control of the reflectivity and position of the reflective area, reducing the impact of spaceborne solar reflection on other areas.

[0054] Based on the fundamental principle of specular reflection, the mirror surface is divided into multiple regions. Using coating technology, the reflectivity of each region can be controlled individually, allowing for adjustment and control of the reflectivity of the reflective area, and even enabling the on / off control of reflection.

[0055] A method for adjusting the angle of the area is also proposed, which can further control the solar reflection angle more precisely. Based on the control of the solar reflection angle of independent areas, the final ground reflection area can be more accurate, and interference from other unnecessary areas can be reduced. It can even achieve the effect of superimposing multiple areas to enhance the light intensity of a certain ground reflection area, thereby better serving those in need.

[0056] It should be understood that the application of the present invention is not limited to the examples above. Those skilled in the art can make improvements or modifications based on the above description, and all such improvements and modifications should fall within the protection scope of the appended claims.

Claims

1. A spaceborne solar reflector, characterized in that, include: At least one onboard reflector and satellite body; The satellite body is set on the satellite orbit and moves along the direction of the satellite orbit to detect the direction of parallel sunlight and adjust the attitude reflection angle between the on-board reflector and the parallel sunlight; The on-board reflector is connected to the satellite body and is perpendicular to the satellite orbit direction. The on-board reflector includes a reflective surface and a backlight plate, and the reflective surface is disposed on the upper surface of the backlight plate. During operation, the backlight panel is located on the side of the on-board reflector away from the parallel sunlight and the Earth's surface; the reflective surface is located on the side of the on-board reflector closer to the parallel sunlight and the Earth's surface, and faces the direction of the parallel sunlight, to reflect the parallel sunlight to the dark areas of the Earth's surface; the satellite body adjusts the attitude and reflection angle of the on-board reflector by adjusting its attitude, and adjusts the intensity of the reflected light from the ground.

2. The spaceborne solar reflector according to claim 1, characterized in that, The on-board reflector is connected to the satellite body via a servo motor; when the servo motor rotates, it drives the on-board reflector to rotate along the servo motor's axis, thereby adjusting the deflection angle between the on-board reflector and parallel sunlight.

3. The spaceborne solar reflector according to claim 1, characterized in that, The reflective surface of the on-board reflector includes: a supporting substrate, a reflective layer, an electrically controlled transmission layer, an adhesive layer, and a quartz protective layer; wherein, The supporting substrate is disposed above the backlight plate of the on-board reflector; The reflective layer is disposed above the supporting substrate and is used to reflect incident parallel sunlight. The electrically controlled transmission layer is disposed above the reflective layer and is electrically connected to the voltage control circuit, used to adjust the reflectivity of the on-board reflector according to the input voltage; The quartz protective layer is located above the electrically controlled transmission layer and is used to protect the reflective surface structure; The adhesive layers are respectively disposed between the supporting substrate and the backlight panel, the reflective layer and the supporting substrate, the electrically controlled transmission layer and the reflective layer, and the quartz protective layer and the electrically controlled transmission layer, for bonding and fixing the supporting substrate and the backlight panel, the reflective layer and the supporting substrate, the electrically controlled transmission layer and the reflective layer, and the quartz protective layer and the electrically controlled transmission layer.

4. The spaceborne solar reflector according to claim 1, characterized in that, The reflective surface includes several adjustable reflective units; the adjustable reflective units are arranged in an array on the upper surface of the backlight panel; each adjustable reflective unit includes: a light-receiving reflective plate, several support columns, and a base; wherein, The edge of the light-receiving reflector is connected to the top of each of the supporting columns with full freedom of movement; The bottom end of the support column is connected to the upper surface of the base with full freedom of movement. The length of the support column is adjustable to adjust the shape and angle of the light-receiving reflector. The base is equipped with a control circuit for controlling the length of the support column, and the lower surface of the base is disposed on the upper surface of the backlight panel.

5. The spaceborne solar reflector according to claim 4, characterized in that, The support column is equipped with a telescopic adjustment structure, which is one of a heating element, a piezoelectric motor, or a micro motor.

6. The spaceborne solar reflector according to claim 1, characterized in that, The satellite body is equipped with a satellite attitude control component, which is used to adjust the attitude reflection angle between the on-board reflector and parallel sunlight by adjusting the overall attitude of the satellite.

7. The spaceborne solar reflector according to claim 4, characterized in that, It also includes a heat-conducting layer, which is disposed on the upper surface of the backlight panel and in contact with the lower surface of the base of each adjustable reflective unit, for absorbing and conducting heat on the adjustable reflective unit.

8. The spaceborne solar reflector according to claim 1, characterized in that, At least one light intensity sensor is disposed on the upper surface of the reflective surface, and the light intensity sensor is used to detect the light intensity of parallel sunlight.

9. A method for controlling spaceborne solar radiation reflection, characterized in that, When the spaceborne solar reflector as described in any one of claims 1-8 is in operation, the method for controlling the spaceborne solar reflector includes the following steps: The satellite body senses the received light intensity on the onboard reflector; The satellite body calculates the initial light intensity based on the received light intensity; The satellite body adjusts its own attitude to adjust the attitude and reflection angle of the onboard reflector, and then adjusts the area of ​​the ground reflection region and the intensity of the ground reflected light according to the initial light intensity.

10. The spaceborne solar radiation reflection control method according to claim 9, characterized in that, A receiving station is set up in the ground reflection area. The receiving station is used to detect the actual ground light intensity over the area of ​​the ground reflection area. After the step of adjusting the area of ​​the ground reflection area and the ground reflected light intensity by adjusting the on-board reflector and the satellite body, the method further includes: The light intensity difference is obtained based on the ground reflected light intensity and the actual ground light intensity, and the attitude reflection angle and deflection angle are adjusted negatively based on the light intensity difference.

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