Ground viewable space display system

Abstract

The application provides a ground-visible space display system and relates to the technical field of satellite display. The system comprises annular display arrays, each annular display array comprises a plurality of satellite stars, the plurality of satellite stars perform relative annular flying motion around a virtual main star, a plurality of annular flying orbits are centered on the virtual main star, and the plurality of annular flying orbits are concentrically nested. The virtual main star is located on an elliptical orbit centered on the earth, the configuration parameters of the satellite stars satisfy a preset condition, and the orbit root number difference between the configuration parameters of the satellite stars and the orbit parameters of the virtual main star satisfies a correlation configuration model. By setting the configuration parameters of the satellite stars and the orbit parameters of the virtual main star, the orbit parameters of the satellite stars are obtained, the annular display arrays are formed, the brightness and color of the light emitting devices on the satellite stars are controlled, the expected display pattern is presented, the observer can see the delivered information without communication media, and global information delivery and transmission can be realized.

Description

Technical Field

[0001] This invention relates to the field of satellite display technology, and more specifically, to a ground-visible space display system. Background Technology

[0002] Display systems are ubiquitous in human society, serving as the core carriers of information transmission and visual presentation. Currently, common display systems include projection screens, CRT monitors, LED arrays, VR glasses, and drone swarms, which are widely used in various fields such as industry, daily life, culture and tourism, and the military. Each system relies on its unique technological principles to meet the display needs of different scenarios.

[0003] The aforementioned representative display devices can all be directly observed by the naked eye, but due to their limited display range, they can only produce media effects within a very limited area, which greatly restricts the wide-area and cross-domain dissemination of information. Summary of the Invention

[0004] The problem that this invention aims to solve is that existing display devices can only generate media effects within an extremely limited area and cannot achieve information transmission over ultra-long distances.

[0005] To address the aforementioned problems, the present invention provides a ground-visible space display system, comprising a ring display array, each ring display array including multiple slave satellites;

[0006] Multiple secondary stars orbit the virtual primary star in relative circular motions, with multiple circular orbits centered on the virtual primary star, and these multiple circular orbits nested around the same center.

[0007] The virtual master star is located in an elliptical orbit centered on Earth. Under preset conditions, the difference in orbital elements between the configuration parameters of the slave stars and the orbital parameters of the virtual master star satisfies the correlation construction model. By setting the configuration parameters of the slave stars and the orbital parameters of the virtual master star, the orbital parameters of the slave stars are obtained. Light-emitting devices are carried on the slave stars, and the brightness and color of the light-emitting devices on each slave star in the ring display array are controlled to form the expected display pattern.

[0008] The configuration parameters of the star include: its circular orbit in Semi-major axis of a planar projection ellipse The semi-minor axis of the projected ellipse Coordinates of the center point of the circular orbit The amplitude of the circular orbit on the z-axis of the LVLH coordinate system From the stars Phase of the plane From the stars Phase in direction ;

[0009] If the circular display array is a multi-layered nested circular array, then the preset conditions include: the x-coordinate of the center point. axis coordinates The ordinate of the center point is zero. axis coordinates Take real numbers, semi-major axis and amplitude Take positive real numbers, , , This represents the phase difference of the transition variable.

[0010] Optionally, the ordinate of the center point axis coordinates The absolute value does not exceed 10km, and the amplitude The maximum value does not exceed 10km; the semi-major axis of the projected ellipse The maximum value does not exceed 10km and is greater than the first preset value, and the distance between stars is greater than the second preset value; ,in, This represents the apparent diameter corresponding to the ground observation dimensions. H This indicates the orbital altitude of the virtual primary star.

[0011] Optionally, the ring orbit of the satellite can be projected into the LVLH coordinate system of the virtual master star, with the observation direction of the ground observer aligned with the x-axis of the LVLH. The observation image seen by the ground observer is the projection of the ring orbit of the satellite about the virtual master star onto the yz plane.

[0012] Optionally, the orbital eccentricity of the virtual primary star e The value is zero or close to zero, and the orbital height is... H The orbital semi-major axis of the virtual primary star is 400km~500km. ,in, The radius is the Earth's radius.

[0013] Optionally, the orbital inclination of the virtual primary star i and coverage of the highest latitude Equal or control the two to approach each other.

[0014] Optionally, the right ascension of the ascending node of the virtual primary star Near the arch point angle Peace Angle The range of values ​​is .

[0015] Optionally, if multiple satellites in the same circular orbit should be evenly distributed, then the following conditions must be met. The values ​​are the same, and two adjacent satellites have the same... , Indicates two adjacent stars in Phase difference in the plane.

[0016] Optionally, the correlation construction model of the orbital element difference is as follows:

[0017]

[0018]

[0019]

[0020]

[0021]

[0022]

[0023] in, This represents the correlation difference between the semi-major axes. This indicates the correlation difference in orbital eccentricity. This indicates the correlation difference in orbital inclination angle. This represents the correlation difference between the ascending nodes and the right ascension. This represents the correlation difference between the near and near angles. This indicates the correlation difference between the near-arch point angles. Represents the arctangent function in quadrants; This represents the semi-major axis of the projected ellipse. Represents the semi-major axis of the virtual primary star's orbit. This represents the orbital eccentricity of the virtual primary star. Indicates from the star Phase of the plane, Indicates the mean anomaly of the virtual primary star. This represents the amplitude of the circular orbital trajectory on the z-axis of the LVLH coordinate system. Indicates the near-aperture angle of the virtual primary star. This represents the ordinate of the center point of the circular orbit. Indicates from the star Phase in direction, This indicates the orbital inclination of the virtual primary star.

[0024] Optionally, the orbital parameters of each satellite are: This is used to complete the satellite array design for the space display system, among which, This represents the right ascension of the ascending node of the virtual primary star.

[0025] Optionally, the configuration of the ring display array can be modified periodically.

[0026] This invention provides a ground-visible space display system. Compared with existing technologies, it has the following advantages:

[0027] Ground-based visible space-based display systems consist of several satellites arranged in a ring in space. This ring array possesses a self-stabilizing physical structure, eliminating the need for frequent maintenance. Each satellite display unit provides a visible light source with controllable brightness and color. The space-based display system provides the physical medium for displaying complex information such as patterns, text, images, and videos in space. Observers can view the transmitted information without communication media, enabling global information delivery and transmission. Attached Figure Description

[0028] 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 these drawings without creative effort.

[0029] Figure 1 A schematic diagram of a ring display array provided in an embodiment of the present invention;

[0030] Figure 2 A schematic diagram of the LVLH coordinate system provided in an embodiment of the present invention;

[0031] Figure 3 This is a schematic diagram of the configuration parameters of the star-ring orbit provided in the LVLH coordinate system according to an embodiment of the present invention;

[0032] Figure 4 This is a schematic diagram of the mapping of a ring satellite array on the yz plane provided in an embodiment of the present invention;

[0033] Figure 5 This is a schematic diagram of the trajectory mapping of a ring satellite array operating on the yz plane for a long time, provided by an embodiment of the present invention.

[0034] Figure 6 This is a schematic diagram of a ring satellite array displayed in the satellite simulation software provided in this embodiment of the invention;

[0035] Figure 7 This is a schematic diagram of a ring satellite array displayed in satellite simulation software after changes over time, provided in an embodiment of the present invention.

[0036] Figure 8 A visual representation of the satellite formation of a circular satellite array provided in an embodiment of the present invention from the ground. Detailed Implementation

[0037] To make the objectives, technical solutions, and advantages of the embodiments of this application clearer, the technical solutions in the embodiments of this application are described clearly and completely. Obviously, the described embodiments are only some embodiments of this application, not all embodiments. Based on the embodiments in this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0038] To better understand the above technical solutions, the following will provide a detailed explanation of the technical solutions in conjunction with the accompanying drawings and specific implementation methods.

[0039] like Figure 1 As shown in the figure, an embodiment of this application provides a ground-visible space display system, including a ring display array, each ring display array including multiple slave satellites;

[0040] Multiple secondary stars orbit the virtual primary star in relative circular motions, with multiple circular orbits centered on the virtual primary star, and these multiple circular orbits nested around the same center.

[0041] The virtual master star is located in an elliptical orbit centered on Earth. Under preset conditions, the difference in orbital elements between the configuration parameters of the slave stars and the orbital parameters of the virtual master star satisfies the correlation construction model. By setting the configuration parameters of the slave stars and the orbital parameters of the virtual master star, the orbital parameters of the slave stars are obtained. Light-emitting devices are carried on the slave stars to control the brightness and color of the light-emitting devices on each slave star in the ring display array to form the expected display pattern.

[0042] Specifically, to form the desired display pattern on the ground, the configuration parameters of the secondary stars (e.g., their instantaneous positions and velocities relative to the virtual primary star) need to meet a series of preset conditions. These conditions may include the relative positional relationships of the secondary stars at a specific moment to ensure they collectively form a recognizable pattern; simultaneously, the brightness requirements of the secondary stars must be met so that they can be clearly seen by ground observers at night or under specific lighting conditions. To achieve these configuration parameters, the orbital element differences between the secondary stars and the virtual primary star are precisely calculated and controlled to satisfy a pre-established correlation construction model. This model considers the orbital state of the virtual primary star and the desired configuration of the secondary stars. By adjusting the orbital elements such as the semi-major axis, eccentricity, and orbital inclination of the secondary stars, multiple secondary stars are distributed as expected in corresponding circular orbits. By controlling the brightness of the secondary stars, a large, ground-visible display pattern is formed in space, thus projecting information. For example, when the virtual primary star passes over a certain area, ground observers in that area can see a specific marker composed of luminous secondary stars. As the virtual main star moves, the relative positions of the secondary stars will also be adjusted accordingly to maintain the integrity and visibility of the pattern, thereby enabling wide-area information display across cities and countries.

[0043] The space display system consists of multiple active-emitting satellites in low Earth orbit. Each satellite, acting as a single display unit, carries its own light-emitting device, which can be an LED lamp payload. This device enables low-power, high-brightness illumination, and its brightness and color are controllable. To meet the requirements for ground-based naked-eye observation, the brightness of the light-emitting device must be less than magnitude 6; the lower the magnitude, the brighter the celestial object. The satellite carries an LED lamp array, which can be observed from the ground when illuminated. This technology has been implemented and validated on the Ladybeetle-I satellite. The Ladybeetle-I satellite, operating at an altitude of 547 km, has a light-emitting payload consisting of an LED array and a lens. It was launched into orbit in December 2018 and completed flashing tests in orbit, flashing according to Morse code rules. Ground-based experiments have shown that the Ladybeetle-I beacon light has a brightness of at least [missing value] within a divergence angle range of ±3°. Brightness higher than that of a zero magnitude star ( The brightness of the beacon light, even in its scattered areas, is easily visible to the naked eye. Therefore, laboratory measurements show that when the Ladybeetle-I satellite is in orbit, the beacon light can be directly observed with the naked eye, and its flight path is visible on clear nights in most Chinese cities (such as Xi'an, Beijing, and Shenzhen). Furthermore, the Ladybeetle-I satellite's on-orbit test report also measured the actual illumination range and brightness of the beacon light. Below the satellite, within a 25km diameter radius centered on the satellite's vertical projection onto the Earth, its light is visible to the human eye; directly below the satellite, the beacon light's brightness is estimated to be -0.6829 magnitude. In conclusion, the Ladybeetle-I satellite, through this example, demonstrates the technical feasibility of ground-based visible light payloads.

[0044] All satellite display units together form a self-stabilizing ring display array. The ring display array consists of one virtual master star and multiple orbiting slave stars. The slave stars orbit the virtual master star in relative orbital motion, with multiple ring orbits centered on the virtual master star. The ring display array is composed of multiple nested ring orbits sharing a common center point. The virtual master star can exist objectively or serve only as a virtual center point in the ring display array design. Several slave stars are evenly distributed on each orbit. A schematic diagram of the ring display array is shown in Figure 1. For example... Figure 1 It contains one main star and three ring orbits with a common center point. From the inside out, each orbit has 3, 6 and 12 secondary stars evenly distributed, respectively. Together, they form a ring display array evenly distributed in space.

[0045] Specifically, such as Figure 3As shown, a schematic diagram of the configuration parameters of the relative ring orbit of the star with respect to the virtual primary star in the LVLH coordinate system is shown below. Figure 3 As shown, For the circular flight track in The semi-major axis of the plane projection ellipse is located at On the axis, Let be the semi-minor axis of the projected ellipse, located at . On the axis, the coordinates of the center point of the circular orbit are , for Amplitude in direction, and They are respectively from the stars plane and Phase in the direction. The plane normal vector relative to the circular orbit is... ,in In conclusion, and This determines the size of the relative circular orbit. and The location of the center point of the relative circular orbit was determined. and The direction of the relative circular flight trajectory was determined. and The phase of the follower star in its relative circular orbit is determined. The semi-major and semi-minor axes determine the shape and size of the circular orbit, while the coordinates of the center point determine the position of the circular orbit relative to the virtual primary star. The amplitude on the z-axis of the LVLH coordinate system controls the range of motion of the follower star in the vertical direction, while the phase of the follower star in the plane and direction determines its specific position in the circular orbit. These parameters can be precisely measured and adjusted using a high-precision navigation system and attitude control system.

[0046] If the circular display array is a multi-layered nested circular array, the preset conditions include: the x-coordinate of the center point. axis coordinates To ensure that the relative circular flight trajectory does not diverge; the ordinate of the center point axis coordinates Take a real number, the y-coordinate of the center point. axis coordinates Take real numbers, semi-major axis and amplitude Take positive real numbers, , , This represents the phase difference of the transition variable.

[0047] In this embodiment, the system constructs a ring-shaped display array through the collaborative operation of multiple satellites, representing a novel form of display carrier. The relative ring-shaped orbital motion of the satellites around the virtual master star, along with the nested orbital design with a common center, makes it possible to form complex and dynamic display patterns in space. This design overcomes the limitation of a single satellite being unable to form complex patterns and avoids the difficulty of controlling complex orbits for numerous independent satellites. Furthermore, the virtual master star, located in an elliptical orbit centered on Earth, provides a stable and predictable macroscopic motion basis for the entire display array, simplifying the orbital control tasks of the satellites. Most importantly, under preset conditions, the orbital element differences between the satellite configuration parameters and the virtual master star satisfy a correlation construction model, providing a method for precisely controlling the satellite formation configuration. This method establishes a mathematical correlation between the orbital element differences between the satellites and the virtual master star to obtain the satellite orbital parameters, ensuring that the satellites can accurately form the display array. Then, the brightness and color of the light-emitting devices on the satellites are controlled to present the desired display pattern, which exhibits good stability and recognizability during ground observation. This correlation construction model based on orbital element differences enables precise control of large-scale satellite formations, thereby achieving high-precision, wide-area visual information presentation in space and effectively solving the technical problem of limited wide-area information dissemination in existing technologies. The ground-visible space display system proposed in this application contains several satellites (i.e., satellite display units) arranged in a ring in space. The resulting ring display array has a self-stabilizing physical structure, eliminating the need for frequent maintenance. Each satellite display unit provides a visible light source with controllable brightness and color. The space display system provides a physical carrier for displaying complex information such as patterns, text, images, and videos in space. It only requires the control center (which can be considered the information transmitter) to send control information to the satellites in the array; no communication needs to be established between the transmitter and receiver (i.e., the observer). Observers can see the transmitted information without a communication medium, enabling global information delivery and transmission.

[0048] In an optional embodiment of this application, to ensure the stability and uniformity of the configuration of the multi-layered nested ring array, the ordinate of the center point is... axis coordinates The absolute value does not exceed 10km, and the amplitude The maximum value does not exceed 10km; the semi-major axis of the projected ellipse The maximum value is no more than 10km and is greater than the first preset value, which can be 2km, 3km or greater; the distance between stars is greater than the second preset value, which can be 73m or greater. ,in, This represents the apparent diameter corresponding to the ground observation dimensions.H This indicates the orbital altitude of the virtual primary star. Additional constraints ensure the visibility and stability of the image.

[0049] In summary, by setting the configuration parameters of the star... The values ​​of the configuration parameters are selected to obtain a ring array space display system with specific geometric characteristics. The configuration parameter values ​​follow the following conditions: (1) They must satisfy the following conditions. (2) and Positive real numbers should be taken, and and The maximum value should not exceed 10km to ensure the accuracy of relative motion. (3) Real numbers should be taken, and The absolute value should not exceed 10km to ensure the accuracy of relative motion. (4) ,when and At that time, the relative circular orbit is in The planar projection is a perfect circle. (5) (6) The value of is related to the apparent diameter observed from the ground. Relevant, should satisfy: The constraints on the center point coordinates and the semi-major and semi-minor axes ensure that the size and position of the circular array are within a controllable range, avoiding excessive image divergence or overlap. The calculation of the apparent diameter is directly related to the ground observation effect, ensuring that the image has sufficient visibility on the ground.

[0050] In an optional embodiment of this application, the orbit of the satellite is projected onto the LVLH coordinate system (Local Vertical Local Horizontal, a local rectangular coordinate system centered on the spacecraft in space dynamics). The observation direction of the ground observer is aligned with the x-axis of the LVLH, and the image seen by the ground observer is the projection of the satellite's orbit about the virtual master star onto the yz plane. The orbital eccentricity of the virtual master star is... e The value is zero or close to zero, and the orbital height is... H The orbital semi-major axis of the virtual primary star is 400km~500km. ,in, The radius is the Earth's radius. The orbital inclination of the virtual primary star is... i and coverage of the highest latitude The two are either equal or controlled to approximate each other. The right ascension of the ascending node of the virtual primary star. Near the arch point angle Peace Angle The range of values ​​is .

[0051] Specifically, the orbital parameters of the space display system are designed as follows: the orbital parameters of the virtual primary star in the Earth-centered inertial frame adopt the semi-major axis. eccentricity Track inclination Right ascension of ascending node Near the arch point angle , and the near point angle To describe. In a space display system, the orbital eccentricity of the virtual primary star should be taken as... This means the virtual primary satellite is located in a circular orbit. To improve the satellite's luminous display effect, minimize light pollution in space, and extend the satellite's lifespan, the virtual primary satellite is located in a near-Earth circular orbit at an altitude of [missing information]. The orbital radius is approximately 300km to 500km, with 400km to 500km being preferable. The semi-major axis of the virtual primary star's orbit is taken as... ,in The radius is the Earth's radius. The orbital inclination of the virtual primary star. This will affect the range of latitudes at which the space display system is visible from Earth, and its orbital inclination. and coverage of the highest latitude Approximately satisfy Right ascension of the ascending node Near the arch point angle , and the near point angle The value only needs to be in Within the specified range.

[0052] Next, we design the configuration parameters of the relative ring orbit of the slave star with respect to the virtual master star. Under the influence of gravity, both the virtual master star and the slave star revolve around the Earth in Keplerian motion. Projecting the trajectory of the slave star onto the LVLH coordinate system of the virtual master star, we can obtain the ring orbit of the slave star with respect to the virtual master star. For example... Figure 2 As shown, the LVLH coordinate system is defined as follows: Origin c Located at the center of mass of the virtual primary star, The axis points in the direction of the position vector r of the virtual master star. The axis points in the direction of the virtual primary star's velocity. The axis points in the direction of the virtual primary star's orbital normal vector, forming a right-handed coordinate system. When the virtual primary star is directly overhead for a ground-based observer, the direction of visual observation is different from that of the LVLH. Since the axes are aligned, the images observed from the ground are essentially derived from the relative motion trajectories of the stars with respect to the virtual primary star. Projection onto a plane.

[0053] The two-dimensional image perceived by ground-based observers is determined by the projection of the satellites onto the plane formed by the y-axis and z-axis in the LVLH coordinate system. This processing method effectively transforms the complex three-dimensional orbital motions in space into two-dimensional images that are easy for ground-based observers to understand and perceive. This greatly simplifies the generation and interpretation of ground-based observation images, improves the real-time performance of image generation, and enables ground-based observers to clearly and accurately perceive the shape and dynamic changes of the ring display array composed of satellites, significantly enhancing the visibility and understandability of the space display system.

[0054] In optional embodiments of this application, such as Figure 3 As shown, the configuration parameters of the satellite include: a circular orbit around the satellite. Semi-major axis of a planar projection ellipse The semi-minor axis of the projected ellipse Coordinates of the center point of the circular orbit The amplitude of the circular orbit on the z-axis of the LVLH coordinate system From the stars Phase of the plane From the stars Phase in direction .

[0055] In an optional embodiment of this application, multiple satellites on the same circular orbit should be evenly distributed to satisfy... The values ​​are the same, and two adjacent satellites have the same... , Indicates two adjacent stars in Phase difference in the plane.

[0056] Specifically, such as Figure 4 As shown, multiple satellites in the same relative circular orbit should be evenly distributed, that is, when When the values ​​are the same, adjacent slave stars should have the same This ensures that the array is evenly distributed, guaranteeing that the ring pattern formed by these stars is visually continuous, complete, and balanced, avoiding local sparseness or density, thereby improving the overall quality and aesthetics of the displayed image.

[0057] In an optional embodiment of this application, based on the virtual primary star orbit parameters and from star configuration parameters The difference in orbital elements between the secondary star and the virtual primary star can be calculated using the following formula. The correlation model for the difference in orbital elements is as follows:

[0058]

[0059]

[0060]

[0061]

[0062]

[0063]

[0064] in, This represents the correlation difference between the semi-major axes. This indicates the correlation difference in orbital eccentricity. This indicates the correlation difference in orbital inclination angle. This represents the correlation difference between the ascending nodes and the right ascension. This represents the correlation difference between the near and near angles. This indicates the correlation difference between the near-arch point angles. Represents the arctangent function with quadrants.

[0065] Based on this, the orbital parameters of each satellite are: The design of the satellite array for the space display system was completed. By defining the orbital parameters of each satellite and using this to design the satellite array, the ground-visible space display system could smoothly transition from the theoretical model stage to the practical deployment stage. This ensures that the satellite array can operate precisely in space according to the preset geometric configuration, thereby guaranteeing the accuracy, stability, and controllability of the displayed patterns seen by ground observers, greatly improving the feasibility and reliability of the space display system's display effects.

[0066] In addition, considering gravity and The simulation, which included perturbations (the primary source of perturbations in low Earth orbit) and atmospheric drag perturbations, determined the relative orbital trajectories and satellite distribution of the satellite formation after 10 hours of simulation. Figure 5 As shown, the satellite formation configuration shows a slight deviation. To eliminate the satellite formation configuration deviation caused by orbital perturbations, the configuration of the circular display array can be periodically corrected. For example, the formation configuration can be maintained through simple orbital control such as orbit lifting, or the configuration parameters of the slave satellites can be retransmitted to correct the positions of the slave satellites in the circular satellite array. The control frequency can be set on a daily basis, and the control frequency is relatively low.

[0067] In summary, compared with existing technologies, it has the following beneficial effects:

[0068] This invention proposes for the first time a ground-based visible space display system based on a ring satellite array. Multiple ring-shaped orbiting satellites form a self-stabilizing satellite array, creating a long-term stable dynamic pixel array that achieves a display effect visible to the naked eye on the ground. Because the satellites are at a much higher altitude than any existing display system, this space display system can simultaneously cover multiple regions for information delivery. Furthermore, unlike internet communication, it can still transmit information even in areas with no signal or sparse population. This invention provides an important technological foundation for building a globally covered broadcast media platform and can be used in various mission scenarios such as cross-regional advertising, large-scale ceremonial performances, disaster relief, and emergency navigation.

[0069] Using a virtual primary star as the reference star, the remaining satellites orbit around the virtual primary star. Multiple orbits are distributed in space with a common center point and on the same plane, and each orbit has a different relative orbital amplitude, forming a multi-layered nested structure. The resulting satellite array is projected onto the LVLH coordinate system. The plane displays a perfect circle. The virtual primary star's orbital parameters are directly set to the values ​​shown in Table 1, with the Earth's radius at 6378.137 km and the orbital altitude H at 500 km.

[0070] Table 1. Virtual primary star orbit parameters for the ring satellite array

[0071]

[0072] A total of three relative orbital paths were established, with three satellites evenly distributed in the innermost layer, six satellites evenly distributed in the middle layer, and twelve satellites evenly distributed in the outermost layer. To ensure a common center point, To ensure nested layers, from the innermost to the outermost layer... The values ​​increase uniformly; to ensure coplanarity, the orbital lengths of each layer are... and All values ​​are equal; to ensure that the ground observation is a perfect circle, take... and Set the star configuration parameters directly to the values ​​shown in Table 2.

[0073] Table 2 Configuration parameters of satellites in a ring satellite array

[0074]

[0075] The orbital parameters of the secondary star were obtained by solving the configuration parameters of the secondary star, the orbital parameters of the virtual primary star, and the associated construction model, as shown in Table 3. It should be noted that the calculated orbital eccentricity of the secondary star... Since it is a very small value, it is directly set to 0 in Table 3; in Table 3, Indicates the semi-major axis of the star's orbit. Indicates the inclination of a star's orbit. Indicates the right ascension from the ascending node of the star. Indicates the angle from the near-circumference point of the star. This indicates the angle from the star's level anterior point.

[0076] Table 3. Slave orbital parameters of the circular satellite array

[0077]

[0078] In the LVLH coordinate system of the virtual primary star, the ring satellite array is distributed as follows: Figure 1 As shown. The mapping of the ring satellite array on the yz plane is as follows. Figure 4 As shown, the ground observation effect presents a nested pattern of multiple layers of perfect circles.

[0079] The generated satellite array orbital parameters are input into satellite simulation software, and the resulting spatial configuration changes over time, as shown below. Figure 6 and Figure 7 As shown, the designed display array consistently orbits the virtual master star uniformly, presenting a regular and orderly array arrangement. The satellite formation configuration remains largely unchanged despite orbital motion. Based on this formation, more complex information displays such as text, patterns, and videos can be achieved by rationally planning the on / off states of the satellite lights.

[0080] Analysis of the visual observation effect of the space display system

[0081] The size of the satellite formation needs to be determined based on the desired effect for naked-eye observation. Specifically, the maximum size of the formation must meet the visual diameter constraint for observation; for example, the visual diameter of a full moon is approximately 0.5°. Simultaneously, to ensure a clear pattern is visible to the naked eye, the satellites in the formation must meet a minimum distance constraint, where the minimum resolvable angle (i.e., the minimum visual diameter) is... The corresponding formation size constraints can be calculated using the following formula:

[0082]

[0083] For example, for satellites orbiting at an altitude of 500km, the minimum inter-satellite distance is approximately 72.72m. Therefore, the inter-satellite distance can be required to be greater than a second preset value, which could be 73m. To achieve the display size of a full moon, the formation radius is approximately 2.18km. To ensure the formation shape is visible from the ground, the outer radius of the ring display array can be required to be greater than a first preset value, which could be 2km or 3km, etc. When designing the formation size, the relevant parameter values ​​can be appropriately increased. Furthermore, the more satellites and satellite orbits there are, the higher the resolution of the display system and the better the visual observation effect.

[0084] The table below shows the naked-eye observation effects of the satellite formations corresponding to the configuration parameters shown, and compares them with the naked-eye observation of the moon. Figure 8As shown in the image, exported from the observation terminal software, this diagram displays the zenith direction at the ground observation point, the visual observation of the satellite formation, and the visual observation of the moon. The maximum designed radius of this formation is approximately 3 km, larger than the apparent diameter of the full moon. Figure 8 It can be seen that the size of the satellite formation is larger than that of the full moon, and the satellite luminous dots are clearly visible in the field of view. Information can be displayed and transmitted by changing the brightness and color of some of the satellite luminous payloads.

[0085] It should be noted that, in this document, relational terms such as "first" and "second" are used only to distinguish one entity or operation from another, and do not necessarily require or imply any such actual relationship or order between these entities or operations. Furthermore, the terms "comprising," "including," or any other variations thereof are intended to cover non-exclusive inclusion, such that a process, method, article, or apparatus that comprises a list of elements includes not only those elements but also other elements not expressly listed, or elements inherent to such a process, method, article, or apparatus. Without further limitations, an element defined by the phrase "comprising one..." does not exclude the presence of other identical elements in the process, method, article, or apparatus that includes said element.

[0086] The above embodiments are only used to illustrate the technical solutions of this application, and are not intended to limit them. Although this application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some of the technical features. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the spirit and scope of the technical solutions of the embodiments of this application.

Claims

1. A ground-visible space display system, characterized in that, It includes a ring display array, each ring display array comprising multiple slave satellites; Multiple secondary stars orbit the virtual primary star in relative circular motions, with multiple circular orbits centered on the virtual primary star, and these multiple circular orbits nested around the same center. The virtual master star is located in an elliptical orbit centered on Earth. Under preset conditions, the difference in orbital elements between the configuration parameters of the slave stars and the orbital parameters of the virtual master star satisfies the correlation construction model. By setting the configuration parameters of the slave stars and the orbital parameters of the virtual master star, the orbital parameters of the slave stars are obtained. Light-emitting devices are carried on the slave stars, and the brightness and color of the light-emitting devices on each slave star in the ring display array are controlled to form the expected display pattern. The configuration parameters of the star include: its circular orbit in Semi-major axis of a planar projection ellipse The semi-minor axis of the projected ellipse Coordinates of the center point of the circular orbit The amplitude of the circular orbit on the z-axis of the LVLH coordinate system From the stars Phase of the plane From the stars Phase in direction ; If the circular display array is a multi-layered nested circular array, then the preset conditions include: the x-coordinate of the center point. axis coordinates The ordinate of the center point is zero. axis coordinates Take real numbers, semi-major axis and amplitude Take positive real numbers, , , Indicates the phase difference of the transition variable; The correlation construction model for the orbital element differences is as follows: ； ； ； ； ； ； in, This represents the correlation difference between the semi-major axes. This indicates the correlation difference in orbital eccentricity. This indicates the correlation difference in orbital inclination. This represents the correlation difference between the ascending nodes and the right ascension. This represents the correlation difference between the near and near angles. This indicates the correlation difference of the near-arch point angle. Represents the arctangent function in quadrants; Represents the semi-major axis of the projected ellipse. Represents the semi-major axis of the virtual primary star's orbit. This represents the orbital eccentricity of the virtual primary star. Indicates from the star Phase of the plane, Indicates the mean anomaly of the virtual primary star. This represents the amplitude of the circular orbital trajectory on the z-axis of the LVLH coordinate system. Indicates the near-aperture angle of the virtual primary star. This represents the ordinate of the center point of the circular orbit. Indicates from the star Phase in direction, This indicates the orbital inclination of the virtual primary star.

2. The ground-visible space display system as described in claim 1, characterized in that, The ordinate of the center point axis coordinates The absolute value does not exceed 10km, and the amplitude The maximum value does not exceed 10km; the semi-major axis of the projected ellipse The maximum value does not exceed 10km and is greater than the first preset value, and the distance between stars is greater than the second preset value; ,in, This represents the apparent diameter corresponding to the ground observation dimensions. H This indicates the orbital altitude of the virtual primary star.

3. The ground-visible space display system as described in claim 1, characterized in that, The circular orbit of the satellite is projected onto the LVLH coordinate system of the virtual primary star. The observation direction of the ground observer is consistent with the x-axis of the LVLH. The observation image seen by the ground observer is the projection of the circular orbit of the satellite about the virtual primary star onto the yz plane.

4. The ground-visible space display system as described in claim 1, characterized in that, The orbital eccentricity of the virtual primary star e The value is zero or close to zero, and the orbital height is... H The orbital semi-major axis of the virtual primary star is 400km~500km. ,in, The radius is the Earth's radius.

5. The ground-visible space display system as described in claim 1, characterized in that, The orbital inclination of the virtual primary star i and coverage of the highest latitude Equal or control the two to approach each other.

6. The ground-visible space display system as described in claim 1, characterized in that, The right ascension of the ascending node of the virtual primary star Near the arch point angle Peace Angle The range of values ​​is .

7. The ground-visible space display system as described in claim 1, characterized in that, If multiple satellites in the same circular orbit are to be evenly distributed, then the following conditions must be met: The values ​​are the same, and two adjacent satellites have the same... , Indicates two adjacent stars in Phase difference in the plane.

8. The ground-visible space display system as described in claim 1, characterized in that, The orbital parameters of each satellite are as follows: This is used to complete the satellite array design for the space display system, among which, This represents the right ascension of the ascending node of the virtual primary star.

9. The ground-visible space display system as described in claim 1, characterized in that, The configuration of the ring display array is periodically modified.

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