Space target deorbit method and device based on diffraction light sail, and electronic equipment

Abstract

The invention discloses a space target deorbiting method and device based on a diffraction light sail and electronic equipment, and relates to the technical field of spaceflight measurement and control, and the space target deorbiting method comprises the steps: configuring the diffraction light sail for a space target, determining the current orbit position of the space target, and determining the position of the space target on the basis of the current orbit position; and determining a first included angle between the velocity vector of the space target and the sun direction vector, determining a diffraction light sail strategy based on an included angle range to which the first included angle belongs, and adjusting a diffraction angle and a sailboard angle of the diffraction light sail by adopting the diffraction light sail strategy so as to drive the space target to deorbit through resistance generated by the adjusted diffraction light sail. The technical problem that the speed of natural deorbit of a space target depending on atmospheric resistance is low in the prior art is solved.

Description

Technical Field

[0001] This invention relates to the field of aerospace telemetry and control technology, and more specifically, to a method, apparatus, and electronic equipment for deorbiting a space target based on a diffractive sail. Background Technology

[0002] Clearing space targets in low Earth orbit is crucial for ensuring the sustainability of space activities. With the explosive growth in the number of spacecraft in low Earth orbit, space debris such as defunct satellites and rocket debris poses an increasingly serious collision threat. This not only endangers the safety of satellites in orbit but may also trigger a "collision chain reaction," or the debris chain reaction described by Kessler's syndrome, ultimately leading to the complete decommissioning of specific orbital regions.

[0003] Currently, most space targets rely on atmospheric drag to deorbit naturally. However, this method has fundamental limitations for targets orbiting above 800 kilometers. At this altitude, the atmospheric density is only one billionth of that at near-Earth altitudes, resulting in negligible drag, and defunct satellites and debris could remain trapped for centuries. Therefore, a method to accelerate the deorbiting of space targets is urgently needed.

[0004] There is currently no effective solution to the above problems. Summary of the Invention

[0005] This invention provides a method, apparatus, and electronic device for deorbiting a space target based on a diffractive sail, to at least solve the technical problem in related technologies where the speed at which a space target deorbits naturally due to atmospheric drag is relatively slow.

[0006] According to one aspect of the present invention, a method for deorbiting a space target based on a diffractive sail is provided, comprising: configuring a diffractive sail for the space target, wherein the diffractive sail is a two-dimensional phase grating composed of multiple periodic grating structures; determining the current orbital position of the space target, and based on the current orbital position, determining a first angle between the velocity vector of the space target and the solar direction vector; determining a diffractive sail strategy based on the angle range to which the first angle belongs; and using the diffractive sail strategy to adjust the diffraction angle and the sail angle of the diffractive sail, so as to drive the space target to deorbit through the drag generated by the adjusted diffractive sail.

[0007] Furthermore, before configuring a diffractive sail for a space target, the process includes: determining the diffraction order of the diffractive sail; and constructing a structural model of the diffractive sail based on the diffraction order, solar wavelength, grating spacing of the diffractive sail, incident angle of sunlight, and diffraction angle of the diffractive sail, wherein the diffraction angle is changed by altering the grating spacing.

[0008] Furthermore, before configuring the diffractive sail for the space target, the process includes: constructing an initial solar radiation pressure calculation model based on the normal of the diffractive sail, the plane direction of the diffractive sail, the diffraction angle of the diffractive sail, the light intensity, and the light speed; determining the second angle between the normal and the direction of sunlight, where the second angle is the angle of the sail plate of the diffractive sail; and adjusting the initial solar radiation pressure calculation model based on the diffraction angle, the second angle, the light intensity, and the light speed to obtain the target solar radiation pressure calculation model.

[0009] Further, the step of determining the diffraction sail strategy based on the included angle range to which the first included angle belongs includes: when the included angle range to which the first included angle belongs is a first preset range, determining a first strategy based on the diffraction sail structure model and the target solar pressure calculation model, and defining the first strategy as the diffraction sail strategy, wherein the first strategy includes: adjusting the diffraction angle based on the first included angle; when the included angle range to which the first included angle belongs is a second preset range, determining a second strategy based on the diffraction sail structure model and the target solar pressure calculation model, and defining the second strategy as the diffraction sail strategy, wherein the second strategy includes: adjusting the sail angle based on the first included angle; when the included angle range to which the first included angle belongs is a third preset range, determining a third strategy based on the diffraction sail structure model and the target solar pressure calculation model, and defining the third strategy as the diffraction sail strategy, wherein the third strategy includes: setting the sail angle to a preset value.

[0010] Furthermore, the steps of adjusting the diffraction angle and the sail angle of the diffraction sail using the diffraction sail strategy include: adjusting the diffraction sail to face the sun when the diffraction sail strategy is the first strategy; determining the current diffraction angle value based on the first included angle; and adjusting the diffraction angle based on the current diffraction angle value.

[0011] Furthermore, the steps of adjusting the diffraction angle of the diffraction sail and the angle of the sail using the diffraction sail strategy include: adjusting the diffraction angle to a fixed value when the diffraction sail strategy is the second strategy; determining the current angle value of the sail based on the first included angle; and adjusting the sail angle based on the current angle value.

[0012] Furthermore, the steps of adjusting the diffraction angle and the sail angle of the diffraction sail using the diffraction sail strategy include: adjusting the sail angle to a preset value when the diffraction sail strategy is the third strategy; and adjusting the diffraction angle to an arbitrary angle value.

[0013] According to another aspect of the present invention, a space target deorbiting device based on a diffractive sail is also provided, comprising: a configuration unit for configuring a diffractive sail for a space target, wherein the diffractive sail is a two-dimensional phase grating composed of multiple periodic grating structures; a first determining unit for determining the current orbital position of the space target and, based on the current orbital position, determining a first angle between the velocity vector of the space target and the solar direction vector; a second determining unit for determining a diffractive sail strategy based on the angle range to which the first angle belongs; and an adjustment unit for adjusting the diffraction angle and the sail angle of the diffractive sail using the diffractive sail strategy, so as to drive the space target deorbiting through the drag generated by the adjusted diffractive sail.

[0014] Furthermore, the space target deorbiting device also includes: a first determining module, used to determine the diffraction order of the diffraction sail before configuring the diffraction sail for the space target; and a first constructing module, used to construct a diffraction sail structural model based on the diffraction order, solar wavelength, grating spacing of the diffraction sail, incident angle of sunlight, and diffraction angle of the diffraction sail, wherein the diffraction angle is changed by changing the grating spacing.

[0015] Furthermore, the space target deorbiting device also includes: a second construction module, used to construct an initial solar pressure calculation model based on the normal of the diffraction sail, the plane direction of the diffraction sail, the diffraction angle of the diffraction sail, the light intensity, and the light speed before configuring the diffraction sail for the space target; a second determination module, used to determine a second angle between the normal and the direction of sunlight, wherein the second angle is the angle of the diffraction sail; and a first adjustment module, used to adjust the initial solar pressure calculation model based on the diffraction angle, the second angle, the light intensity, and the light speed to obtain the target solar pressure calculation model.

[0016] Further, the second determining unit includes: a third determining module, used to determine a first strategy based on the diffraction sail structure model and the target solar pressure calculation model when the included angle range to which the first included angle belongs is a first preset range, and to determine the first strategy as a diffraction sail strategy, wherein the first strategy includes: adjusting the diffraction angle based on the first included angle; a fourth determining module, used to determine a second strategy based on the diffraction sail structure model and the target solar pressure calculation model when the included angle range to which the first included angle belongs is a second preset range, and to determine the second strategy as a diffraction sail strategy, wherein the second strategy includes: adjusting the sail angle based on the first included angle; and a fifth determining module, used to determine a third strategy based on the diffraction sail structure model and the target solar pressure calculation model when the included angle range to which the first included angle belongs is a third preset range, and to determine the third strategy as a diffraction sail strategy, wherein the third strategy includes: setting the sail angle to a preset value.

[0017] Furthermore, the adjustment unit includes: a second adjustment module, used to adjust the diffraction sail to face the sun when the diffraction sail strategy is the first strategy; a sixth determination module, used to determine the current diffraction angle value based on the first included angle; and a third adjustment module, used to adjust the diffraction angle based on the current diffraction angle value.

[0018] Furthermore, the adjustment unit also includes: a fourth adjustment module, used to adjust the diffraction angle to a fixed value when the diffraction sail strategy is the second strategy; a seventh determination module, used to determine the current sail angle value based on the first included angle; and a fifth adjustment module, used to adjust the sail angle based on the current sail angle value.

[0019] Furthermore, the adjustment unit also includes: a sixth adjustment module, used to adjust the sail angle to a preset value when the diffraction sail strategy is the third strategy; and a seventh adjustment module, used to adjust the diffraction angle to an arbitrary angle value.

[0020] According to another aspect of the present invention, a computer program product is also provided, including a non-volatile computer-readable storage medium storing a computer program, wherein the computer program, when executed by a processor, implements the above-described method for deorbiting a space target based on a diffraction sail.

[0021] According to another aspect of the present invention, an electronic device is also provided, including one or more processors and a memory, the memory being used to store one or more programs, wherein when the one or more programs are executed by the one or more processors, the one or more processors cause the one or more processors to implement any of the above-described methods for deorbiting space targets based on diffraction sails.

[0022] In this invention, a diffractive sail is configured for a space target, the current orbital position of the space target is determined, and based on the current orbital position, a first angle between the velocity vector of the space target and the solar direction vector is determined. Based on the range of the first angle, a diffractive sail strategy is determined. By adopting the diffractive sail strategy, the diffraction angle and the sail angle are adjusted so that the drag generated by the adjusted diffractive sail drives the space target to de-orbit, thereby solving the technical problem in related technologies that the speed at which space targets naturally de-orbit due to atmospheric drag is relatively slow.

[0023] This invention employs a diffractive solar sail configuration. By dynamically adjusting the sail's diffraction angle and tilt angle, it maximizes the use of solar radiation pressure as drag to actively deorbit low-Earth orbit targets. This improves the deorbit efficiency of failed satellites and space debris, and solves the technical problems of slow natural decay of high-Earth orbit targets and poor thrust direction control flexibility of traditional reflective solar sails. Specifically, a two-dimensional diffractive solar sail composed of a periodic grating structure can be equipped on the space target. By calculating the relative position of the sail and sunlight, the diffraction angle and tilt angle of the sail are adaptively adjusted to ensure that solar radiation pressure always acts in the opposite direction to the space target's motion. This accelerates orbital decay without consuming any propellant, effectively clearing orbital resources. Attached Figure Description

[0024] The accompanying drawings, which are included to provide a further understanding of the invention and form part of this invention, illustrate exemplary embodiments of the invention and are used to explain the invention, but do not constitute an undue limitation of the invention. In the drawings:

[0025] Figure 1 This is a flowchart of an optional method for deorbiting a space target based on a diffraction sail, according to an embodiment of the present invention.

[0026] Figure 2 This is a schematic diagram of the diffraction of light by an optional diffractive light sail according to an embodiment of the present invention;

[0027] Figure 3 This is a schematic diagram of a simulation of the optical pressure reduction effect at an optional orbital altitude of 600 km according to an embodiment of the present invention;

[0028] Figure 4 This is a schematic diagram of a simulation of the optical pressure reduction effect at an optional orbital altitude of 800 km according to an embodiment of the present invention;

[0029] Figure 5 This is a schematic diagram of an optional space target deorbiting device based on a diffraction sail according to an embodiment of the present invention;

[0030] Figure 6 This is a hardware structure block diagram of an electronic device (or mobile device) for a space target deorbiting method based on a diffraction sail, according to an embodiment of the present invention. Detailed Implementation

[0031] To enable those skilled in the art to better understand the present invention, the technical solutions of the present invention will be clearly and completely described below with reference to the accompanying drawings of the embodiments of the present invention. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort should fall within the scope of protection of the present invention.

[0032] It should be noted that the terms "first," "second," etc., used in this invention are used to distinguish similar objects and are not necessarily used to describe a specific order or sequence. It should be understood that such data can be interchanged where appropriate so that the embodiments of the invention described herein can be implemented in orders other than those illustrated or described herein. Furthermore, the terms "comprising" and "having," and any variations thereof, are intended to cover non-exclusive inclusion; for example, a process, method, system, product, or apparatus that comprises a series of steps or units is not necessarily limited to those steps or units explicitly listed, but may include other steps or units not explicitly listed or inherent to such processes, methods, products, or apparatus.

[0033] It should be noted that all related information (including but not limited to user device information, user personal information, etc.) and data (including but not limited to data used for analysis, stored data, and displayed data) collected and involved in this invention are information and data authorized by the user or fully authorized by all parties. Furthermore, the collection, storage, use, processing, transmission, provision, disclosure, and application of this data comply with the relevant laws, regulations, and standards of the relevant regions, necessary confidentiality measures have been taken, and it does not violate public order and good morals. Corresponding operation entry points are provided for users to choose to authorize or refuse. For example, this system has an interface with relevant users or organizations. Before obtaining relevant information, a request to obtain the information needs to be sent to the aforementioned user or organization through the interface, and the relevant information is obtained only after receiving consent from the aforementioned user or organization.

[0034] To address the limitation of current atmospheric density inversion techniques, which are only applicable to circular orbit satellites, this invention proposes an active deorbiting method for space targets based on the optical pressure drag of a diffractive solar sail. The method includes: designing a diffractive solar sail for the space target; calculating the solar pressure exerted on the space target; adjusting the solar sail angle and diffraction angle according to the direction of the optical pressure and the velocity of the space target to maximize its drag effect; and simulating and verifying the optical pressure deorbiting strategy. This method is applicable to atmospheric density inversion for various orbit types and can improve the spatiotemporal resolution and accuracy of atmospheric density inversion.

[0035] The present invention will now be described in detail with reference to various embodiments.

[0036] Example 1

[0037] According to an embodiment of the present invention, an embodiment of a method for deorbiting a space target based on a diffractive sail is provided. It should be noted that the steps shown in the flowchart in the accompanying drawings can be executed in a computer system such as a set of computer-executable instructions. Furthermore, although a logical order is shown in the flowchart, in some cases, the steps shown or described may be executed in a different order than that shown here.

[0038] Figure 1 This is a flowchart of an optional space target deorbiting method based on a diffraction sail according to an embodiment of the present invention, as shown below. Figure 1 As shown, the method includes the following steps:

[0039] Step S101: Configure a diffractive sail for the space target, wherein the diffractive sail is a two-dimensional phase grating composed of multiple periodic grating structures.

[0040] In this embodiment of the invention, a specially designed diffractive optical sail can be equipped for space targets such as defunct satellites or space debris. The surface of the sail membrane of the diffractive optical sail is covered with periodically arranged micro- and nano-grating structures. These structures enable sunlight to diffract rather than simply reflect as it passes through. This two-dimensional phase grating design allows for control of the direction of light diffraction by adjusting the distance between the grating lines (d) and the sail angle (α), based on the characteristics of the grating and the wavelength of sunlight, thereby changing the direction of the solar radiation pressure experienced by the sail. Compared to conventional reflective optical sails, diffractive optical sails can more flexibly adjust the solar radiation pressure, making it an effective drag under specific conditions and accelerating the deorbiting process of space targets.

[0041] Step S102: Determine the current orbital position of the space target, and based on the current orbital position, determine the first angle between the velocity vector of the space target and the solar direction vector.

[0042] In this embodiment of the invention, the precise orbital position and velocity vector of a space target can be determined using the spacecraft's orbital dynamics model and real-time spacecraft tracking data. Then, the angle between the velocity vector and the solar direction vector (i.e., the vector pointing from the space target to the sun) is calculated and denoted as the first angle (…). This angle directly affects the direction and magnitude of the solar radiation pressure, and how the solar sail most effectively utilizes the solar radiation pressure to generate drag.

[0043] Step S103: Determine the diffraction sail strategy based on the angle range to which the first included angle belongs.

[0044] In this embodiment of the invention, based on the first included angle For different values ​​of , an adaptive light sail strategy is proposed. When the angle is between 0° and 35°, with the sail facing the sun, the drag effect is maximized by adjusting the diffraction angle (θ) so that the direction of the light pressure is opposite to the velocity vector. Between 35° and 125°, in addition to adjusting the diffraction angle to its maximum value, the sail tilt angle (α) also needs to be adjusted to keep the light pressure in the opposite direction of the velocity, ensuring maximum drag. When the angle exceeds 125° to 180°, solar radiation pressure cannot generate effective drag. The design goal is to minimize solar radiation pressure in the velocity direction. Adjusting the angle α of the sail so that the normal of the sail is perpendicular to the sunlight reduces the projection of the radiation pressure in the velocity direction and avoids adverse acceleration effects.

[0045] Step S104: Adopt a diffraction sail strategy, adjust the diffraction angle of the diffraction sail and the angle of the sail plate, so as to drive the space target off-orbit through the drag generated by the adjusted diffraction sail.

[0046] In this embodiment of the invention, the diffraction angle θ and the sail angle α of the diffraction sail are dynamically adjusted according to a determined solar sail strategy to ensure that solar radiation pressure always acts as drag on the space target. This adjustment process requires a precise control mechanism and a deep understanding of orbital dynamics to maximize the radiation pressure in a specific direction, thereby accelerating the orbital decay of the space target and achieving active deorbiting. Through meticulous control of the solar sail, even in high orbits where atmospheric drag is weak, additional braking force can be effectively generated, significantly shortening the target's orbital dwell time and providing a new solution for clean space environment and orbital resource management.

[0047] Through the above steps, a diffractive sail and its flexible light pressure direction control can be used to provide an active deorbiting method for failed or retired space targets without consuming their own energy or propellant, effectively avoiding long-term orbital occupation and collision risks, and promoting the sustainable development of space activities.

[0048] In summary, by configuring a diffractive solar sail and dynamically adjusting the sail's diffraction angle and tilt angle, the goal of maximizing the use of solar radiation pressure as drag to actively deorbit low-Earth orbit space targets can be achieved. This improves the deorbiting efficiency of failed satellites and space debris, and solves the technical problems of slow natural decay of high-Earth orbit targets and poor thrust direction control flexibility of traditional reflective solar sails. Specifically, a two-dimensional diffractive solar sail composed of a periodic grating structure can be equipped on the space target. By calculating the relative position of the sail and sunlight, the diffraction angle and tilt angle of the sail can be adaptively adjusted to ensure that solar radiation pressure always acts in the opposite direction to the space target's motion. This accelerates orbital decay without consuming any propellant and effectively clears orbital resources.

[0049] To improve the accuracy of constructing the diffractive sail structure model, in the space target deorbiting method based on the diffractive sail provided in Embodiment 1 of this application, the diffraction order of the diffractive sail is determined before configuring the diffractive sail for the space target; based on the diffraction order, solar wavelength, grating spacing of the diffractive sail, incident angle of sunlight, and diffraction angle of the diffractive sail, the diffraction sail structure model is constructed, wherein the diffraction angle is changed by changing the grating spacing.

[0050] In this embodiment of the invention, solar radiation pressure refers to the pressure generated by the momentum transfer when solar photons strike the surface of an object, and its direction is parallel to the sunlight. Traditional solar sails are reflective sails, and their working principle follows the law of reflection. After a photon strikes a smooth, mirror-like sail film, it is reflected back by the mirror. According to the law of conservation of momentum, the change in the photon's momentum exerts a force on the sail, and the direction of this force is perpendicular to the sail surface. The magnitude of the solar radiation pressure can be adjusted by changing the angle of the sail surface; that is, the solar radiation pressure is greatest when the sail surface is perpendicular to the sunlight, and the solar radiation pressure is minimum when the sail surface is parallel to the sunlight. The limitation of this type of reflective sail is that it can only generate normal radiation pressure. Diffractive sails, on the other hand, can control the direction of diffracted light by adjusting the direction and arrangement of the microstructures on the sail surface, thereby obtaining solar radiation pressure with variable direction. Figure 2 This is a schematic diagram of the diffraction of light by an optional diffractive light sail according to an embodiment of the present invention, as shown below. Figure 2 As shown, when the angle of incidence is At that time, the angle of the diffracted ray is ,in, .

[0051] In this embodiment of the invention, the surface of the diffractive solar sail is not a smooth mirror, but rather composed of countless tiny, periodic grating structures, which can be considered a two-dimensional "phase grating." When light passes through a slit or grating whose size is close to or smaller than the wavelength, it undergoes wave bending and diffusion; this phenomenon is diffraction. The diffractive solar sail works as follows: Sunlight (as an electromagnetic wave) penetrates the micro-nano structure of the sail, producing a controllable phase delay on the passing light wave; when the light wave exits from the other side of the sail, these precisely modulated phase delays cause the wavefront of the entire light wave to be distorted and rearranged; according to the Huygens-Fresnel principle, this reconstructed wavefront does not primarily propagate forward, but is deflected to one or more specific angles, similar to a prism dispersing white light into a rainbow, but a diffraction grating can achieve more precise and efficient directional control. According to Newton's third law, if the photon stream is systematically deflected in a new direction, then the sail itself must be subjected to a force of equal magnitude and opposite direction. In a diffractive optical sail, the change in momentum of a photon is the vector difference between its initial direction and the final diffraction direction. Therefore, the direction of the generated optical pressure is not necessarily perpendicular to the sail surface, but is opposite to the direction of the net change in momentum of the photon.

[0052] Limited by the grating equation and the overall diffraction efficiency of materials for the solar spectrum, the ability of a diffraction sail to change the direction of light pressure is not unlimited; that is, it is impossible to achieve a 180-degree reversal of the force direction. In order to meet the requirement that solar radiation pressure always serves as a drag on space targets, the structure of the diffraction sail should be rationally designed to maximize its ability to change light.

[0053] The diffraction grating equation determines the grating diffraction angle. The formula is as follows: Where m is the diffraction order, usually first-order diffraction is used, i.e., m=±1; λ is the wavelength of light; and d is the grating spacing, i.e., the period of the grating. It is the angle of incidence of light.

[0054] Under the condition of space target orientation towards the sun The above formula can be simplified to: For a given solar wavelength, the angle of light diffraction can be changed by altering the grating line spacing *d*. The peak wavelength of sunlight is approximately 500-600 nanometers; theoretically, a diffraction angle of -90 to 90 degrees can be obtained using a nanometer-scale grating with a grating line spacing comparable to the wavelength. Considering diffraction efficiency and engineering feasibility, The maximum value is set to reach 70 degrees.

[0055] Specifically, the diffraction order of the diffraction sail can be determined first. The diffraction order (m) refers to a specific order among the multiple diffracted beams generated by the diffraction grating. Usually, the first order diffraction is the focus, i.e., m = ±1, because the intensity of the first-order diffracted light is typically the strongest, while the intensity of higher or lower orders decreases rapidly, which is not conducive to generating sufficient optical pressure. Choosing an appropriate diffraction order ensures that the diffraction sail can achieve maximum efficiency in optical pressure propulsion. Then, based on the diffraction order m, the solar wavelength λ, the grating line spacing d of the diffraction sail, and the incident angle of the sunlight... and the diffraction angle of the diffraction sail A diffractive sail structure model was constructed.

[0056] To control the direction of solar radiation pressure, the grating spacing *d* of the diffraction sail needs to be dynamically adjusted based on the diffraction order *m*, the solar wavelength *λ*, and the desired diffraction angle *θ*. Adjusting *d* requires comprehensive consideration of factors such as grating manufacturing limitations, diffraction efficiency, and structural rigidity. By precisely adjusting the grating spacing, the direction of solar radiation pressure can be changed to any desired angle, thus maximizing the conversion of radiation pressure into the required drag at different orbital positions and solar azimuth angles.

[0057] In this embodiment, a highly adaptable and flexible diffractive optical sail system can be provided for space targets at different orbital positions. Based on real-time orbital information and sunlight conditions, the system adaptively adjusts the diffraction structure of the optical sail, ensuring that the light pressure always acts in the opposite direction to the target's motion, thus consistently acting as a decelerating drag. This not only provides an effective means of accelerating the decay of high-orbit targets but also ensures that even under conditions of thin atmosphere and negligible natural drag, space targets can be actively and effectively guided into lower orbits until they are eventually deorbited, significantly improving the efficiency and reliability of orbit clearing.

[0058] To improve the accuracy of determining the target solar pressure calculation model, in the space target deorbiting method based on a diffractive sail provided in Embodiment 1 of this application, before configuring the diffractive sail for the space target, an initial solar pressure calculation model is constructed based on the normal of the diffractive sail, the plane direction of the diffractive sail, the diffraction angle of the diffractive sail, the light intensity, and the light speed; a second angle between the normal and the direction of sunlight is determined, wherein the second angle is the angle of the sail plate of the diffractive sail; based on the diffraction angle, the second angle, the light intensity, and the light speed, the initial solar pressure calculation model is adjusted to obtain the target solar pressure calculation model.

[0059] In this embodiment of the invention, the normal direction based on the diffraction sail... The plane direction of the diffraction sail Using the diffraction angle θ of the diffraction sail, the intensity I of sunlight, and the speed of light c, an initial solar pressure calculation model is constructed to calculate the solar pressure vector generated by the diffraction sail. The expression for this model is:

[0060] ;

[0061] in, Let I be the light pressure vector, and c be the light intensity and the speed of light. For the solar sail normal, This refers to the direction of the solar sail plane. The direction of the generated solar radiation pressure. The angle between the sail and the normal is .

[0062] In this embodiment of the invention, the normal line of the sailboard is... The angle between the angle and the direction of sunlight (i.e., the second angle) is determined as follows: (Sail angle of the diffractive sail). Here, the second included angle, or sail angle (α), refers to the angle between the normal of the diffractive sail and the direction of sunlight. At different orbital positions, the direction of sunlight changes with the motion of the space target. Therefore, by monitoring and calculating the direction of sunlight in real time, the optimal tilt angle of the sail under current conditions can be determined to ensure that solar radiation pressure energy is most effectively converted into deceleration drag. The calculation of the second included angle is crucial when adjusting the sail strategy, as it affects the projection of the radiation pressure vector onto the velocity direction of the space target, i.e., the actual magnitude of the drag felt.

[0063] After determining the second included angle (α), the initial solar radiation pressure calculation model can be adjusted to account for the influence of the solar panel tilt on the radiation pressure direction. By modifying the expression for the radiation pressure vector in the initial model and introducing the second included angle (α) and diffraction angle (θ), a more accurate target solar radiation pressure calculation model reflecting the actual situation is obtained. .

[0064] In this embodiment, the tilt attitude and diffraction angle of the diffractive sail can be dynamically adjusted to ensure that solar radiation pressure always provides optimal drag, accelerating the deorbiting process of space targets. This not only improves deorbiting efficiency, especially for high-orbit targets with weak atmospheric drag, but also avoids the consumption of fuel or working fluid in traditional propulsion methods.

[0065] To improve the accuracy of determining the diffractive sail strategy, in the space target deorbiting method based on a diffractive sail provided in Embodiment 1 of this application, when the included angle range to which the first included angle belongs is a first preset range, a first strategy is determined based on the diffractive sail structure model and the target solar pressure calculation model, and the first strategy is determined as the diffractive sail strategy. The first strategy includes: adjusting the diffraction angle based on the first included angle. When the included angle range to which the first included angle belongs is a second preset range, a second strategy is determined based on the diffractive sail structure model and the target solar pressure calculation model, and the second strategy is determined as the diffractive sail strategy. The second strategy includes: adjusting the sail angle based on the first included angle. When the included angle range to which the first included angle belongs is a third preset range, a third strategy is determined based on the diffractive sail structure model and the target solar pressure calculation model, and the third strategy is determined as the diffractive sail strategy. The third strategy includes: setting the sail angle to a preset value.

[0066] In this embodiment of the invention, the velocity vector of the spatial target is assumed to be... The angle between the vector and the direction of the sun (pointing towards the sun) is... (First included angle), windsurfing normal The angle with the direction of sunlight is (Sailboat angle). When a space target is in different orbital positions, i.e. The adjustment strategy (diffraction sail strategy) of the light sail differs depending on the range of values.

[0067] Specifically, in the relative positional relationship between the space target and the sun, the first included angle... The range from 0° to 35° is considered the first preset range. Within this range, the line connecting the space target and the sun is almost perpendicular to the target's direction of motion, meaning that sunlight can directly act on the maximum effective area of ​​the solar sail. The purpose of the first strategy is to adjust the diffraction angle (θ) so that the direction of solar radiation pressure is precisely opposite to the target's velocity, thereby maximizing the deceleration effect.

[0068] When the first included angle Within the range of 35° to 125°, i.e., within the second preset range, adjusting only the diffraction angle is insufficient to ensure that the solar radiation pressure always acts in the opposite direction of the target's movement. The purpose of the second strategy is to combine the adjustment of the sail tilt angle α to further control the direction of the solar radiation pressure and maintain its effective resistance to the target's forward movement. This strategy is implemented by setting the sail diffraction angle θ to its maximum value while simultaneously adjusting the sail tilt angle α... -35°, this adjustment ensures that even when there is an angle between the direction of sunlight and the target velocity vector, the direction of light pressure remains consistent with the direction of velocity through appropriate tilting of the solar sail, achieving the effect of deceleration and deorbiting. This strategy, along with... As the speed increases, the tilt of the sail also increases accordingly, and the projection of the effective sail area in the opposite direction of the speed gradually decreases. However, the drag effect of light pressure can still be maintained through strategy adjustments.

[0069] When the first included angle Within the range of 125° to 180°, falling into the third preset range, the direction of sunlight is almost in the same or opposite direction as the motion of the space target, significantly reducing the direct drag effect. The third strategy is designed to minimize the direct sunlight exposure to the sail in this extreme situation, avoiding any acceleration that would be detrimental to deorbiting. This third strategy is implemented by setting the sail tilt angle α to a preset value of 90°, meaning the edge of the sail faces the sunlight directly. The diffraction angle θ can be set to any value. Since the edge of the sail is now facing the sun, the projection of sunlight onto the sail surface is almost zero, ensuring that the sunlight pressure does not adversely affect the target's deorbiting motion.

[0070] In this embodiment, the diffraction angle and tilt angle of the solar sail can be intelligently adjusted according to the relative position of the space target and the sun under different orbital environments, ensuring that solar radiation pressure is converted into deceleration drag in the optimal form at all times. This improves the efficiency and controllability of deorbiting failed satellites and space debris, especially in high-orbit regions, overcoming the problem of weak natural atmospheric drag without consuming any propellant or energy.

[0071] In order to accurately adjust the diffraction angle and the angle of the diffraction sail, in the space target deorbiting method based on the diffraction sail provided in Embodiment 1 of this application, when the diffraction sail strategy is the first strategy, the diffraction sail is adjusted to face the sun; based on the first included angle, the current diffraction angle value is determined; and based on the current diffraction angle value, the diffraction angle is adjusted.

[0072] In this embodiment of the invention, Within the range (i.e., the first preset range), the thrust can be aligned perfectly with the opposite direction of the velocity by adjusting the diffraction angle. Position the sail directly towards the sun and adjust the diffraction angle. At this time, the direction of solar radiation pressure The pressure from sunlight is precisely directed in the opposite direction of the speed, and the drag is always at its maximum. Recorded as ,in, .

[0073] Specifically, by adjusting the sail normal of the diffractive sail to align with the direction of sunlight, i.e., setting the sail angle α to 0°, the diffractive sail is fully exposed to sunlight to receive maximum intensity of sunlight. Through a high-precision pointing control system, the sail can be precisely aligned with the sun, ensuring the accuracy of subsequent light pressure calculations and strategy execution. Then, based on the current orbital information of the space target, the first included angle is calculated. When the first included angle falls within a first preset range (0° to 35°), the formula is used... The current diffraction angle θ of the solar sail is determined. Here, θ represents the angle by which the diffraction direction of sunlight changes due to the microstructure on the sail surface, and is a key parameter for controlling the direction of solar radiation pressure. This ensures that the solar radiation pressure acts in the direction most favorable to slowing down the target velocity, thereby accelerating the deorbiting process. After determining the current diffraction angle θ, the grating structure of the diffraction sail is adjusted so that its microstructure can produce a diffraction effect matching θ. This is achieved by adjusting the nanoscale grating spacing d on the sail surface to conform to the diffraction grating equation. By changing d, the diffraction direction of sunlight can be precisely controlled, ensuring that the direction of the light pressure vector is consistent with the opposite direction of the velocity vector of the space target, thereby maximizing the use of solar radiation pressure as drag and accelerating the target's orbital decay.

[0074] In this embodiment, it is possible to achieve the first strategy, i.e., the first included angle. Within a range of 0° to 35°, efficient adaptive adjustment of the diffraction sail is achieved. First, the sail is positioned directly facing the sun to ensure that the sail receives maximum solar radiation pressure. Then, the diffraction angle is dynamically calculated and adjusted based on the first included angle, enabling the sail to accurately convert solar radiation pressure into braking force.

[0075] In order to accurately adjust the diffraction angle and the sail angle of the diffraction sail, in the space target deorbiting method based on the diffraction sail provided in Embodiment 1 of this application, when the diffraction sail strategy is the second strategy, the diffraction angle is adjusted to a fixed value; the current sail angle value is determined based on the first included angle; and the sail angle is adjusted based on the current sail angle value.

[0076] In this embodiment of the invention, Within the range (i.e., the second preset range), it is impossible to align the thrust perfectly with the negative direction of velocity simply by adjusting the diffraction angle; it is necessary to combine this with sail deflection to maximize drag. Adjusting the diffraction angle... Adjust the angle of the windsurfing board At this moment, the direction of solar radiation pressure is exactly opposite to the direction of velocity, and the drag is... ,in, ,along with Increase and decrease, when At that time, the resistance is zero.

[0077] Specifically, regardless of the current value of the first included angle, the diffraction angle (θ) is adjusted to the maximum allowable value, typically set to 70°. This fixed value is chosen based on the diffraction efficiency of the grating material to the solar spectrum and engineering feasibility considerations. By setting θ to 70°, it ensures that even... Within a relatively wide range, the solar sail can also control the diffraction direction of sunlight as much as possible. Then, the first included angle is calculated based on the real-time orbital information of the space target. .exist Under conditions between 35° and 125°, based on the formula The current value of the solar panel angle α is obtained. This allows for the quantification of the optimal tilt of the solar panel relative to the sun's direction, maximizing the projection of solar radiation pressure in the opposite direction of velocity, thus achieving maximum deceleration. Subsequently, based on the calculated current solar panel angle value α, the diffraction sail is precisely adjusted. Through actuators, such as precision motors or hydraulic arms, the solar panel is tilted to the required angle, ensuring that the resultant force of the solar radiation pressure is opposite to the direction of motion of the space target, thus acting as an effective braking force. This adjustment process needs to be synchronized with the orbital motion of the space target to ensure timely changes in the solar panel angle to adapt to the constantly changing... Value, maintaining continuous and efficient light pressure resistance.

[0078] In this embodiment, at the first included angle Under conditions ranging from 35° to 125°, by setting the diffraction angle to its maximum value and optimizing the solar panel angle, the problem of insufficient natural atmospheric drag was effectively overcome, providing a powerful propulsion for the active deorbiting of high-orbit space targets. This strategy allows the solar radiation pressure direction to be calibrated to the ideal deceleration position even when there is a certain deviation between the solar radiation pressure direction and the target velocity direction, through dynamic adjustment of the solar panel angle.

[0079] In order to accurately adjust the diffraction angle and the sail angle of the diffraction sail, in the space target deorbiting method based on the diffraction sail provided in Embodiment 1 of this application, when the diffraction sail strategy is the third strategy, the sail angle is adjusted to a preset value; and the diffraction angle is adjusted to an arbitrary angle value.

[0080] In this embodiment of the invention, Within the specified range (i.e., the third preset range), solar radiation pressure cannot generate effective drag; the design goal is to minimize solar radiation pressure in the velocity direction. Adjusting the sail angle so that the sail's normal is perpendicular to the sunlight... The diffraction angle can be set to any angle, at which point the light pressure is zero.

[0081] Specifically, when the diffractive sail strategy adopts the third strategy, i.e., the first included angle... Within the third preset range of 125° to 180°, regardless of the first included angle The specific values ​​all involve setting the sail angle α to a preset value of 90°. This means the sail's edge is aligned with the sun, with the edge of the sail directly facing the sun, and the normal to the sail perpendicular to the direction of sunlight. By placing the sail at this specific angle, the effective effect of sunlight pressure on the target's direction of motion is greatly reduced, avoiding [damage / impact]. This refers to a situation where solar radiation pressure actually accelerates space targets when the value is in an unfavorable range. After setting the sail angle to a preset value of 90°, the diffraction angle θ can be adjusted to any angle. Although... When the value is in the range of 125° to 180°, the drag effect of direct light pressure is limited. However, by adjusting θ, the microstructure of the light sail surface can still be changed. Even if this change is not very effective in reducing the deviation of the light pressure direction, it will at least not have a negative impact on the overall performance of the light sail. This degree of freedom provides the possibility for future fine-tuning or to deal with unforeseen situations.

[0082] In this embodiment, at the first included angle Under conditions ranging from 125° to 180°, by stabilizing the solar panel angle α at a preset value of 90° and allowing arbitrary adjustment of the diffraction angle θ, it is ensured that the space target will not accelerate due to solar radiation pressure regardless of changes in the direction of sunlight, thus avoiding any adverse effects on the active deorbiting process. This strategy is particularly suitable for situations where, under specific orbital phases, the natural direction of solar radiation pressure conflicts with the required drag direction. Stable solar panel attitude and flexible diffraction angle control guarantee the stability and safety of the solar sail system under any illumination conditions. Simultaneously, this attitude control strategy simplifies the management complexity of the solar sail, reduces the risks of on-orbit operation, and provides reliable technical support for the effective active deorbiting of high-orbit space targets. Under this strategy, the space target can operate stably along a predetermined orbital decay path with minimal solar radiation pressure interference until final deorbiting.

[0083] The following section provides a detailed explanation of the active deorbiting scheme for space targets based on the optical pressure drag of a diffractive sail, as described in this embodiment, in conjunction with simulation verification.

[0084] The solar beam deorbiting strategy of this embodiment was simulated and verified, with the satellite mass set to 400 kg and the solar sail area to 10 m². 2 The simulation investigated the orbit decay at initial orbital altitudes of 600km and 800km.

[0085] Figure 3 This is a schematic diagram illustrating a simulation of the optical pressure reduction effect at an optional orbital altitude of 600 km according to an embodiment of the present invention. Figure 3 As shown, a simulation effect curve was established with time (days) as the horizontal axis and orbital altitude (km) as the vertical axis, demonstrating the simulation results of natural attenuation and optical pressure reduction orbit. Simulating a one-year flight time, with an initial orbit of 600km, the orbital altitude naturally attenuated by 46.3km, while the orbital altitude attenuated by the optical pressure reduction orbit strategy attenuated by 55.7km, representing an increase in attenuation rate of 20.3%.

[0086] Figure 4 This is a schematic diagram illustrating a simulation of the optical pressure reduction effect at an optional orbital altitude of 800 km according to an embodiment of the present invention. Figure 4 As shown, a simulation effect curve was established with time (days) as the horizontal axis and orbital altitude (km) as the vertical axis, demonstrating the simulation results of natural attenuation and optical pressure reduction orbit. Simulating a one-year flight time, with an initial orbit of 800km, the orbital altitude naturally attenuated by 3.48km, while the orbital altitude attenuated by the optical pressure reduction orbit strategy attenuated by 17.5km, a fourfold increase in attenuation.

[0087] In this embodiment of the invention, a diffractive solar sail is configured. By dynamically adjusting the diffraction angle and tilt angle of the sail, the maximum utilization of solar radiation pressure as drag to actively deorbit low-Earth orbit space targets is achieved. This improves the deorbit efficiency of failed satellites and space debris, and solves the technical problems of slow natural decay of high-Earth orbit targets and poor thrust direction control flexibility of traditional reflective solar sails. Specifically, a two-dimensional diffractive solar sail composed of a periodic grating structure can be equipped on the space target. By calculating the relative position of the sail and sunlight, the diffraction angle and tilt angle of the sail are adaptively adjusted to ensure that solar radiation pressure always acts in the opposite direction to the space target's motion. This accelerates orbital decay without consuming any propellant and effectively clears orbital resources.

[0088] The following is a detailed description with reference to another embodiment.

[0089] Example 2

[0090] The space target deorbiting device based on a diffraction sail provided in this embodiment includes multiple implementation units, each of which corresponds to a specific implementation step in Embodiment 1 above.

[0091] Figure 5 This is a schematic diagram of an optional space target deorbiting device based on a diffraction sail according to an embodiment of the present invention, as shown below. Figure 5 As shown, the space target deorbiting device may include: a configuration unit 50, a first determination unit 51, a second determination unit 52, and an adjustment unit 53.

[0092] The configuration unit 50 is used to configure a diffractive sail for a space target, wherein the diffractive sail is a two-dimensional phase grating composed of multiple periodic grating structures.

[0093] The first determining unit 51 is used to determine the current orbital position of the space target, and based on the current orbital position, determine the first angle between the velocity vector of the space target and the solar direction vector;

[0094] The second determining unit 52 is used to determine the diffraction sail strategy based on the angle range to which the first included angle belongs;

[0095] The adjustment unit 53 is used to adopt a diffraction sail strategy to adjust the diffraction angle and the sail angle of the diffraction sail, so as to drive the space target off-orbit through the drag generated by the adjusted diffraction sail.

[0096] The aforementioned space target deorbiting device can employ a diffractive solar sail. By dynamically adjusting the sail's diffraction angle and tilt angle, it maximizes the use of solar radiation pressure as drag to actively deorbit low-Earth orbit space targets. This improves the deorbiting efficiency of failed satellites and space debris, and solves the technical problems of slow natural decay of high-Earth orbit targets and poor thrust direction control flexibility of traditional reflective solar sails. Specifically, a two-dimensional diffractive solar sail composed of a periodic grating structure can be equipped on the space target. By calculating the relative position of the sail and sunlight, the diffraction angle and tilt angle of the sail are adaptively adjusted to ensure that solar radiation pressure always acts in the opposite direction to the space target's motion. This accelerates orbital decay without consuming any propellant, effectively clearing orbital resources.

[0097] Optionally, the space target deorbiting device further includes: a first determining module, used to determine the diffraction order of the diffraction sail before configuring the diffraction sail for the space target; and a first constructing module, used to construct a diffraction sail structural model based on the diffraction order, solar wavelength, grating spacing of the diffraction sail, incident angle of sunlight, and diffraction angle of the diffraction sail, wherein the diffraction angle is changed by changing the grating spacing.

[0098] Optionally, the space target deorbiting device further includes: a second construction module, used to construct an initial solar pressure calculation model based on the normal of the diffraction sail, the plane direction of the diffraction sail, the diffraction angle of the diffraction sail, the light intensity, and the light speed before configuring the diffraction sail for the space target; a second determination module, used to determine a second angle between the normal and the direction of sunlight, wherein the second angle is the angle of the sail plate of the diffraction sail; and a first adjustment module, used to adjust the initial solar pressure calculation model based on the diffraction angle, the second angle, the light intensity, and the light speed to obtain a target solar pressure calculation model.

[0099] Optionally, the second determining unit includes: a third determining module, used to determine a first strategy based on the diffraction sail structure model and the target solar pressure calculation model when the included angle range to which the first included angle belongs is a first preset range, and to determine the first strategy as a diffraction sail strategy, wherein the first strategy includes: adjusting the diffraction angle based on the first included angle; a fourth determining module, used to determine a second strategy based on the diffraction sail structure model and the target solar pressure calculation model when the included angle range to which the first included angle belongs is a second preset range, and to determine the second strategy as a diffraction sail strategy, wherein the second strategy includes: adjusting the sail angle based on the first included angle; and a fifth determining module, used to determine a third strategy based on the diffraction sail structure model and the target solar pressure calculation model when the included angle range to which the first included angle belongs is a third preset range, and to determine the third strategy as a diffraction sail strategy, wherein the third strategy includes: setting the sail angle to a preset value.

[0100] Optionally, the adjustment unit includes: a second adjustment module for adjusting the diffraction sail to face the sun when the diffraction sail strategy is the first strategy; a sixth determination module for determining the current diffraction angle value based on the first included angle; and a third adjustment module for adjusting the diffraction angle based on the current diffraction angle value.

[0101] Optionally, the adjustment unit further includes: a fourth adjustment module, used to adjust the diffraction angle to a fixed value when the diffraction sail strategy is the second strategy; a seventh determination module, used to determine the current sail angle value based on the first included angle; and a fifth adjustment module, used to adjust the sail angle based on the current sail angle value.

[0102] Optionally, the adjustment unit further includes: a sixth adjustment module, used to adjust the sail angle to a preset value when the diffraction sail strategy is the third strategy; and a seventh adjustment module, used to adjust the diffraction angle to an arbitrary angle value.

[0103] The aforementioned space target deorbiting device may also include a processor and a memory. The configuration unit 50, the first determining unit 51, the second determining unit 52, the adjustment unit 53, etc., are all stored in the memory as program units, and the processor executes the aforementioned program units stored in the memory to realize the corresponding functions.

[0104] The aforementioned processor contains a kernel, which retrieves the corresponding program units from memory. One or more kernels can be configured, and by adjusting kernel parameters, a diffraction sail strategy can be employed. This involves adjusting the diffraction angle and sail angle of the diffraction sail to drive the space target off-orbit using the drag generated by the adjusted diffraction sail.

[0105] The aforementioned memory may include non-permanent memory in computer-readable media, such as random access memory (RAM) and / or non-volatile memory, such as read-only memory (ROM) or flash RAM, and the memory includes at least one memory chip.

[0106] The present invention also provides a computer program product, which, when executed on a data processing device, is suitable for executing an initialization program having the following method steps: configuring a diffractive sail for a space target, determining the current orbital position of the space target, and based on the current orbital position, determining a first angle between the velocity vector of the space target and the solar direction vector, determining a diffractive sail strategy based on the angle range to which the first angle belongs, adopting the diffractive sail strategy, and adjusting the diffraction angle and the sail angle of the diffractive sail so as to drive the space target off-orbit through the drag generated by the adjusted diffractive sail.

[0107] According to another aspect of the present invention, a computer program product is also provided, including a non-volatile computer-readable storage medium storing a computer program, wherein the computer program, when executed by a processor, implements the above-described method for deorbiting a space target based on a diffraction sail.

[0108] According to another aspect of the present invention, an electronic device is also provided, including one or more processors and a memory, the memory being used to store one or more programs, wherein when the one or more programs are executed by the one or more processors, the one or more processors cause the one or more processors to implement the above-described method for deorbiting a space target based on a diffraction sail.

[0109] Figure 6 This is a hardware structure block diagram of an electronic device (or mobile device) for a space target deorbiting method based on a diffraction sail, according to an embodiment of the present invention. Figure 6 As shown, an electronic device may include one or more processors (e.g., Figure 6 The processors 602a, 602b, ..., 602n, etc., may include, but are not limited to, processing devices such as microprocessors (MCUs) or programmable logic devices (FPGAs), and a memory 604 for storing data. In addition, it may include: a display, an input / output interface (I / O interface), a universal serial bus (USB) port (which may be included as one of the ports of the I / O interface), a network interface, a keyboard, a power supply, and / or a camera. Those skilled in the art will understand that... Figure 6 The structure shown is for illustrative purposes only and does not limit the structure of the electronic device described above. For example, the electronic device may also include components that are more... Figure 6 The more or fewer components shown, or having the same Figure 6 The different configurations shown.

[0110] The sequence numbers of the above embodiments of the present invention are for descriptive purposes only and do not represent the superiority or inferiority of the embodiments.

[0111] The embodiments or examples disclosed herein are not exhaustive, but merely illustrative of some embodiments or examples, and are not intended to limit the scope of protection of this disclosure. Unless otherwise specified, each step in a particular embodiment or example can be implemented as an independent embodiment, and the steps can be arbitrarily combined. For example, a solution after removing some steps in a particular embodiment or example can also be implemented as an independent embodiment, and the order of the steps in a particular embodiment or example can be arbitrarily interchanged. Furthermore, optional methods or examples in a particular embodiment or example can be arbitrarily combined; moreover, embodiments or examples can be arbitrarily combined. For example, some or all steps of different embodiments or examples can be arbitrarily combined, and a particular embodiment or example can be arbitrarily combined with optional methods or examples of other embodiments or examples.

[0112] In the above embodiments of the present invention, the descriptions of each embodiment have different focuses. For parts not described in detail in a certain embodiment, please refer to the relevant descriptions of other embodiments.

[0113] In the several embodiments provided by this invention, it should be understood that the disclosed technical content can be implemented in other ways. The device embodiments described above are merely illustrative; for example, the division of units can be a logical functional division, and in actual implementation, there may be other division methods. For example, multiple units or components may be combined or integrated into another system, or some features may be ignored or not executed. Furthermore, the displayed or discussed mutual coupling, direct coupling, or communication connection can be through some interfaces; the indirect coupling or communication connection of units or modules can be electrical or other forms.

[0114] The units described as separate components may or may not be physically separate. The components shown as units may or may not be physical units; that is, they may be located in one place or distributed across multiple units. Some or all of the units can be selected to achieve the purpose of this embodiment according to actual needs.

[0115] Furthermore, the functional units in the various embodiments of the present invention can be integrated into one processing unit, or each unit can exist physically separately, or two or more units can be integrated into one unit. The integrated unit can be implemented in hardware or as a software functional unit.

[0116] If the integrated unit is implemented as a software functional unit and sold or used as an independent product, it can be stored in a computer-readable storage medium. Based on this understanding, the technical solution of the present invention, in essence, or the part that contributes to the prior art, or all or part of the technical solution, can be embodied in the form of a software product. This computer software product is stored in a storage medium and includes several instructions to cause a computer device (which may be a personal computer, server, or network device, etc.) to execute all or part of the steps of the methods described in the various embodiments of the present invention. The aforementioned storage medium includes various media capable of storing program code, such as USB flash drives, read-only memory (ROM), random access memory (RAM), portable hard drives, magnetic disks, or optical disks.

[0117] The above description is only a preferred embodiment of the present invention. It should be noted that for those skilled in the art, several improvements and modifications can be made without departing from the principle of the present invention, and these improvements and modifications should also be considered within the scope of protection of the present invention.

Claims

1. A method for deorbiting a space target based on a diffractive optical sail, characterized in that, include: A diffractive sail is configured for a space target, wherein the diffractive sail is a two-dimensional phase grating composed of multiple periodic grating structures; Determine the current orbital position of the space target, and based on the current orbital position, determine the first angle between the velocity vector of the space target and the solar direction vector; Based on the range of included angles to which the first included angle belongs, determine the diffraction sail strategy; By employing the diffraction sail strategy, the diffraction angle and sail angle of the diffraction sail are adjusted so that the drag generated by the adjusted diffraction sail drives the space target off-orbit.

2. The method for deorbiting a space target according to claim 1, characterized in that, Before configuring diffractive sails for space targets, the following is also included: Determine the diffraction order of the diffraction sail; Based on the diffraction order, solar wavelength, grating spacing of the diffraction sail, incident angle of sunlight, and diffraction angle of the diffraction sail, a diffraction sail structural model is constructed, wherein the diffraction angle is changed by changing the grating spacing.

3. The method for deorbiting a space target according to claim 1, characterized in that, Before configuring diffractive sails for space targets, the following is also included: Based on the normal of the diffraction sail, the planar direction of the diffraction sail, the diffraction angle of the diffraction sail, the light intensity, and the light speed, an initial solar radiation pressure calculation model is constructed. Determine the second angle between the normal and the direction of sunlight, wherein the second angle is the angle of the sail of the diffractive sail; Based on the diffraction angle, the second included angle, the light intensity, and the light speed, the initial solar radiation pressure calculation model is adjusted to obtain the target solar radiation pressure calculation model.

4. The method for deorbiting a space target according to claim 1, characterized in that, The steps for determining the diffraction sail strategy based on the range of included angles to which the first included angle belongs include: When the included angle range to which the first included angle belongs is a first preset range, a first strategy is determined based on the diffraction sail structure model and the target solar radiation pressure calculation model, and the first strategy is determined as the diffraction sail strategy, wherein the first strategy includes: adjusting the diffraction angle based on the first included angle; When the included angle range to which the first included angle belongs is a second preset range, a second strategy is determined based on the diffractive sail structure model and the target solar radiation pressure calculation model, and the second strategy is determined as the diffractive sail strategy, wherein the second strategy includes: adjusting the angle of the sail based on the first included angle; When the included angle range to which the first included angle belongs is a third preset range, a third strategy is determined based on the diffractive sail structure model and the target solar pressure calculation model, and the third strategy is determined as the diffractive sail strategy, wherein the third strategy includes: setting the sail angle to a preset value.

5. The method for deorbiting a space target according to claim 4, characterized in that, The steps of adjusting the diffraction angle and the sail angle using the aforementioned diffraction sail strategy include: When the diffractive sail strategy is the first strategy, the diffractive sail is adjusted to face the sun; Based on the first included angle, determine the current diffraction angle value; Adjust the diffraction angle based on the current diffraction angle value.

6. The method for deorbiting a space target according to claim 4, characterized in that, The steps of adjusting the diffraction angle and the sail angle using the aforementioned diffraction sail strategy include: When the diffraction sail strategy is the second strategy, the diffraction angle is adjusted to a fixed value; Based on the first included angle, the current windshield angle value is determined. Adjust the angle of the windsurfing board based on the current windsurfing angle value.

7. The method for deorbiting a space target according to claim 4, characterized in that, The steps of adjusting the diffraction angle and the sail angle using the aforementioned diffraction sail strategy include: When the diffractive sail strategy is the third strategy, the angle of the sail is adjusted to the preset value; Adjust the diffraction angle to any value.

8. A space target deorbiting device based on a diffractive sail, characterized in that, include: A configuration unit is used to configure a diffractive sail for a space target, wherein the diffractive sail is a two-dimensional phase grating composed of multiple periodic grating structures; The first determining unit is used to determine the current orbital position of the space target, and based on the current orbital position, determine the first angle between the velocity vector of the space target and the solar direction vector; The second determining unit is used to determine the diffraction sail strategy based on the angle range to which the first included angle belongs; An adjustment unit is used to adjust the diffraction angle and the angle of the diffraction sail using the diffraction sail strategy, so as to drive the space target off-orbit through the drag generated by the adjusted diffraction sail.

9. A computer program product, characterized in that, The method includes a non-volatile computer-readable storage medium storing a computer program that, when executed by a processor, implements the space target deorbiting method based on any one of claims 1 to 7.

10. An electronic device, characterized in that, It includes one or more processors and a memory, the memory being used to store one or more programs, wherein when the one or more programs are executed by the one or more processors, the one or more processors cause the one or more processors to implement the space target deorbiting method based on any one of claims 1 to 7.

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