A method for enhancing space-based optical imaging of satellite devices and space targets

Abstract

The present invention relates to a satellite device and a space-based optical imaging enhancement method for a space target. The satellite device includes: a cabin; a target solar wing, the target solar wing being connected to a posture adjustment mechanism fixed to the cabin via a corresponding deployment arm, and having a mirror reflection film attached to the back of the target solar wing, and a laser radar imaging device also mounted on the target solar wing; an imaging enhancement guidance unit, the imaging enhancement guidance unit being encapsulated in a system management unit of a satellite integrated electronic subsystem, the imaging enhancement guidance unit being used to control the deployment arm and the posture adjustment mechanism to direct the central axis of the back of the target solar wing toward the space target based on the angular information of the space target obtained by the laser radar imaging device, so as to guide the mirror reflection film to reflect sunlight onto the observation surface of the space target, and to control the laser radar imaging device to observe and image the space target. With the help of the above technical solution, the embodiments of the present application can effectively improve imaging quality.

Description

Technical Field

[0001] The present invention relates to the technical field of optical imaging of space targets, and in particular to a satellite device and a space-based optical imaging enhancement method for space targets. Background Art

[0002] Space-based optical imaging technology has extremely important value and significance in the fields of spacecraft troubleshooting and operation status review.

[0003] In optical imaging, the photometric properties of space targets are one of the primary characteristics currently used for observation and identification by space-based optical imaging systems. Constrained by space lighting conditions, when a satellite actively approaches a space target, low irradiance on the target's imaging surface significantly increases the difficulty of imaging. Even if front-lit observation conditions are achieved through mission planning, irradiance polarization may occur in the target's observed area (e.g., parts of the image may be extremely bright or dark) due to occlusion by large structures on the satellite. This can result in the loss of numerous target details, leading to technical issues such as poor imaging. Summary of the Invention

[0004] (1) Technical issues to be resolved

[0005] In view of the above-mentioned shortcomings and deficiencies of the prior art, the present invention provides a space-based optical imaging enhancement method for satellite devices and space targets, which solves the technical problem of poor imaging effect in the prior art.

[0006] (2) Technical solution

[0007] In order to achieve the above objectives, the main technical solutions adopted by the present invention include:

[0008] In a first aspect, an embodiment of the present invention provides a satellite device, comprising: a cabin; a target solar wing, the target solar wing being connected to a posture adjustment mechanism fixed on the cabin through a corresponding deployment arm, and a mirror reflection film being affixed to the back of the target solar wing, and a laser radar imaging device being also installed on the target solar wing; an imaging enhancement guidance unit, the imaging enhancement guidance unit being encapsulated in a system management unit of a satellite integrated electronic subsystem, the imaging enhancement guidance unit being used to control the deployment arm and the posture adjustment mechanism to point the central axis of the back of the target solar wing toward the space target based on the angle information of the space target obtained by the laser radar imaging device, so as to guide the mirror reflection film to reflect sunlight onto the observation surface of the space target, and to control the laser radar imaging device to observe and image the space target.

[0009] In a possible embodiment, the mirror reflection film includes a substrate, a transition layer disposed on the substrate, a reflection layer disposed on the transition layer, and a protection layer disposed on the reflection layer.

[0010] In a possible embodiment, the thickness of the substrate is 98-102 μm, the thickness of the transition layer is 0.02-0.04 μm, the thickness of the reflective layer is 0.1-0.2 μm, and the thickness of the protective layer is 4-6 μm.

[0011] Preferably, the thickness of the substrate is 100 μm (ie, 100 micrometers), the thickness of the transition layer is 0.03 μm, the thickness of the reflective layer is 0.15 μm, and the thickness of the protective layer is 5 μm.

[0012] In a possible embodiment, the material of the substrate is polyimide or ultra-thin glass, the material of the transition layer is Cr or aluminum oxide, the material of the reflective layer is Ag, and the material of the protective layer is silicon dioxide.

[0013] In one possible embodiment, the deployment arm includes a base joint, an elbow joint, and a wrist joint.

[0014] In a second aspect, an embodiment of the present invention provides a space-based optical imaging enhancement method for a space target, which is applied to an imaging enhancement guide unit of a satellite device such as any one of the first aspects; the space-based optical imaging enhancement method includes: obtaining angle information of the space target obtained by a laser radar imaging device of the satellite device; according to the angle information, controlling the posture adjustment mechanism and the deployment arm of the satellite device to point the central axis of the back of the target solar wing of the satellite device toward the space target, so as to guide the mirror reflection film attached to the back of the target solar wing to reflect sunlight onto the observation surface of the space target; and controlling the laser radar imaging device to observe and image the space target.

[0015] In one possible embodiment, based on the angle information, the position adjustment mechanism and the deployment arm of the satellite device are controlled to point the central axis of the back side of the target solar wing of the satellite device toward the space target, including: before the satellite device enters the fine adjustment range, based on the angle information, the position adjustment mechanism and the deployment arm are controlled to roughly point the central axis of the back side of the target solar wing toward the space target; based on the position feedback of the deployment arm and the angle information of the space target obtained by the laser radar imaging device, it is judged whether the satellite device has entered the fine adjustment range; if it is determined that the satellite device has entered the fine adjustment range, the position adjustment mechanism and the deployment arm are controlled to accurately point the central axis of the back side of the target solar wing toward the space target.

[0016] In one possible embodiment, controlling the posture adjustment mechanism and the deployment arm to precisely point the central axis of the back side of the target solar wing toward the space target includes: acquiring displacement data collected by a displacement sensor of a satellite device; determining whether precise pointing has been achieved based on the displacement data and angle information of the space target acquired by a lidar imaging device; and if precise pointing has not been achieved, continuing to control the posture adjustment mechanism and the deployment arm to precisely point the central axis of the back side of the target solar wing toward the space target until precise pointing is achieved.

[0017] In one possible embodiment, before controlling the satellite device's posture adjustment mechanism and deployment arm to direct the central axis of the back side of the satellite device's target solar wing toward the space target based on the angle information, the space-based optical imaging enhancement method further includes: obtaining jitter information of the surface of the target solar wing; and controlling the satellite device's stabilization control mechanism to correct the direction of the solar wing surface based on the jitter information.

[0018] In a third aspect, an embodiment of the present application provides a storage medium having a computer program stored thereon, and the computer program is executed by a processor to execute the method described in the second aspect or any optional implementation of the second aspect.

[0019] In a fourth aspect, an embodiment of the present application provides an electronic device comprising: a processor, a memory and a bus, wherein the memory stores machine-readable instructions executable by the processor. When the electronic device is running, the processor and the memory communicate through the bus, and when the machine-readable instructions are executed by the processor, the method described in the second aspect or any optional implementation of the second aspect is executed.

[0020] In a fifth aspect, the present application provides a computer program product, which, when running on a computer, enables the computer to execute the method in the second aspect or any possible implementation of the second aspect.

[0021] (3) Beneficial effects

[0022] The beneficial effects of the present invention are:

[0023] The present invention provides a space-based optical imaging enhancement method for a satellite device and a space target. The method adds a mirror reflection film, a laser radar imaging device and an imaging enhancement guidance unit to the standard configuration of a satellite. The mirror reflection film can be pasted on the back of a solar wing, the laser radar imaging device can be installed on the solar wing, and the imaging enhancement guidance unit can be encapsulated in a system management unit of a satellite integrated electronic subsystem. Therefore, imaging enhancement can be achieved without changing the satellite form and without adding additional burden.

[0024] In order to make the above-mentioned objectives, features and advantages to be achieved by the embodiments of the present application more obvious and easy to understand, preferred embodiments are specifically cited below and described in detail with reference to the accompanying drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0025] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the following is a brief introduction to the drawings required for use in the embodiments of the present application. It should be understood that the following drawings only show certain embodiments of the present application and therefore should not be regarded as limiting the scope. For ordinary technicians in this field, other relevant drawings can be obtained based on these drawings without creative work.

[0026] Figure 1 A schematic diagram of a satellite device provided in an embodiment of the present application is shown;

[0027] Figure 2 A schematic diagram of a deployment arm provided in an embodiment of the present application is shown;

[0028] Figure 3 A schematic diagram of a posture adjustment mechanism provided in an embodiment of the present application is shown;

[0029] Figure 4 A schematic diagram of a mirror reflective film provided in an embodiment of the present application is shown;

[0030] Figure 5 A flow chart of a space-based optical imaging enhancement method for a space target provided in an embodiment of the present application is shown. DETAILED DESCRIPTION

[0031] In order to better explain the present invention and facilitate understanding, the present invention is described in detail below through specific implementation methods in conjunction with the accompanying drawings.

[0032] In order to solve the problem of poor imaging effect in the prior art, an embodiment of the present application provides a space-based optical imaging enhancement method for satellite devices and space targets. By adding a mirror reflection film, a lidar imaging device and an imaging enhancement guide unit on the basis of the standard satellite configuration (for example, the satellite may include two solar wings, two deployment arms and two posture adjustment mechanisms, etc.), and the mirror reflection film can be pasted on the back of the solar wing, and the lidar imaging device can be installed on the solar wing, and the imaging enhancement guide unit can also be packaged in the system management unit of the satellite integrated electronic subsystem, so that imaging enhancement can be achieved without changing the satellite shape and adding additional burden.

[0033] To better understand the above technical solutions, exemplary embodiments of the present invention will be described in more detail below with reference to the accompanying drawings. Although exemplary embodiments of the present invention are shown in the accompanying drawings, it should be understood that the present invention can be implemented in various forms and should not be limited by the embodiments described herein. Instead, these embodiments are provided to enable a clearer and more thorough understanding of the present invention and to fully convey the scope of the present invention to those skilled in the art.

[0034] See Figure 1 , Figure 1 FIG. 1 shows a schematic diagram of a satellite device provided in an embodiment of the present application. Figure 1 The satellite device shown includes: a cabin; a target solar wing, which is connected to a posture adjustment mechanism fixed on the cabin through a corresponding deployment arm, and a mirror reflection film is affixed to the back of the target solar wing, and a laser radar imaging device is also installed on the target solar wing; an imaging enhancement guidance unit, which is encapsulated in a system management unit of the satellite integrated electronic subsystem, and the imaging enhancement guidance unit is used to control the deployment arm and the posture adjustment mechanism to point the central axis of the back of the target solar wing toward the space target based on the angle information of the space target obtained by the laser radar imaging device, so as to guide the mirror reflection film to reflect sunlight onto the observation surface of the space target, and control the laser radar imaging device to observe and image the space target.

[0035] It should be noted that the laser radar imaging device can be called a radar device, and the radar device can be a high-precision radar. In addition, the laser radar imaging device can be installed on both the front and back of the target solar wing.

[0036] It should be understood that the specific solar wing of the target solar wing, the specific structure of the deployment arm, the specific structure of the posture adjustment mechanism, the specific structure of the mirror reflection film, the installation position of the lidar imaging device and its specific mechanism and the specific unit form of the imaging enhancement guide unit can all be set according to actual needs, and the embodiments of the present application are not limited to this.

[0037] Alternatively, if the satellite device includes multiple solar wings, the target solar wing may be at least one of the multiple solar wings, and a mirror reflective film may be attached to the back of the target solar wing. The front of the target solar wing may be provided with multiple photoelectric conversion devices.

[0038] For example, Figure 1 As shown, in the case where the satellite device includes two solar wings, one of the two solar wings can be used as the target solar wing.

[0039] Optionally, the end of the deployment arm may be connected to the edge of the solar wing, and the root of the deployment arm may be connected to a posture adjustment mechanism fixed to the cabin.

[0040] Furthermore, the deployment arm has a total of 4 degrees of freedom, and may include: a base joint, which can rotate and drive the upper arm to deploy the target solar wing (also known as a reflective mirror, also known as a mirror reflective film, etc.) from the side of the spacecraft (also known as a satellite device); an elbow joint, which can rotate and drive the forearm to assist in adjusting the deployment arm's posture outside the spacecraft; and two joints are set at the wrist to respectively realize pitch and roll movements, driving the reflector to complete the task of directional tracking. And the specific structure of the deployment arm can be found in Figure 2 Deployment arms shown.

[0041] Alternatively, see Figure 3 , Figure 3 A schematic diagram of a posture adjustment mechanism provided by an embodiment of the present application is shown, and the posture adjustment can be achieved through one-dimensional axial motion of three linear motors.

[0042] It should be noted here that the specific connection method between the posture adjustment mechanism and the deployment arm can be set according to actual needs, and the embodiments of the present application are not limited to this.

[0043] For example, the specific connection method between the posture adjustment mechanism and the deployment arm can be achieved through existing connection methods.

[0044] Furthermore, the position adjustment mechanism can actively adjust the backside orientation of the target solar wing. When the satellite device is performing a space target observation mission sent from the ground, it can obtain real-time jitter information of the target solar wing through high-frequency precision measurement. The position adjustment mechanism can also correct the backside orientation of the target solar wing, thereby improving the accuracy and stability of the system. Furthermore, the reflector surface can be adjusted through a mechanical device to control the tilt and swing of the target solar wing. This allows for integrated closed-loop measurement and adjustment of the position adjustment mechanism based on the relationship between the reflector's adjustment capability and changes in the space environment.

[0045] Alternatively, see Figure 4 , Figure 4 FIG. 1 shows a schematic diagram of a mirror reflective film provided in an embodiment of the present application. Figure 4 As shown, the mirror reflection film may include a substrate, a transition layer disposed on the substrate, a reflection layer disposed on the transition layer, and a protection layer disposed on the reflection layer.

[0046] It should be understood that the specific material and design parameters of the substrate, the specific material and design parameters of the transition layer, the specific material and design parameters of the reflective layer, and the specific material and design parameters of the protective layer can all be set according to actual needs, and the embodiments of the present application are not limited to this.

[0047] For example, the mirror reflective film can use polyimide or ultra-thin glass as a substrate, and Ag can be plated on the surface to achieve a high reflectivity of 95% across a wide wavelength band from 500nm to 6μm. The Ag film can also be plated with SiO2 as a protective layer to prevent degradation in the environment. To improve adhesion, Cr or Al2O3 can be added as a transition layer between the substrate and the Ag film. The mirror reflective film's substrate can be bonded to the thin film structure on the back of the solar wing.

[0048] For another example, the thickness of the substrate is 98-102 μm, the thickness of the transition layer is 0.02-0.04 μm, the thickness of the reflective layer is 0.1-0.2 μm, and the thickness of the protective layer is 4-6 μm. Preferably, the thickness of the substrate is 100 μm, the thickness of the transition layer is 0.03 μm, the thickness of the reflective layer is 0.15 μm, and the thickness of the protective layer is 5 μm.

[0049] Alternatively, as Figure 1 As shown, a laser radar imaging device is fixed at the center position of the back side of the target solar wing (for example, when the shape of the target solar wing is circular, the center of the circle is the center of the target solar wing, etc.).

[0050] For example, during the installation of a LiDAR imaging device, the laser lens assembly can be mounted on the solar wing. Be careful not to remove the lens protective cover during installation. This installation must be completed before the satellite system installs payloads and other heavy equipment to prevent structural deformation and the effects of gravity on installation accuracy.

[0051] Optionally, the imaging enhancement guidance unit can be encapsulated in the system management unit of the integrated electronic subsystem and installed at a designated location in the cabin after analyzing the equipment layout in the cabin.

[0052] Therefore, with the help of the above-mentioned technical solution, the embodiment of the present application addresses the problem of difficulty in imaging dark areas of the target in a harsh lighting environment. The mirror reflection film pasted on the back of the target solar wing reflects the sunlight energy to the observation surface of the space target, thereby increasing the irradiance of the imaging surface and achieving the effect of enhanced imaging of the dark areas of the target.

[0053] In addition, in order to address the problem of "yin-yang face" when the satellite approaches for detailed inspection, the embodiment of the present application uses the device to perform fill-light imaging to obtain more target details and achieve the effect of enhanced imaging of complex configuration space targets.

[0054] It should be understood that the above description of the satellite device is merely exemplary, and those skilled in the art may make various modifications to the relevant parts of the device according to actual needs, and the modified solutions also fall within the scope of protection of this application.

[0055] In order to facilitate understanding of the relevant execution process of the imaging enhancement guidance unit, a specific embodiment is described below.

[0056] Specifically, see Figure 5 , Figure 5 FIG. 1 shows a flow chart of a space-based optical imaging enhancement method for a space target provided by an embodiment of the present application. Figure 5 The space-based optical imaging enhancement method shown can be applied to an imaging enhancement guidance unit of a satellite device, which can be the satellite device described above. For details, please refer to the relevant description above. Specifically, the space-based optical imaging enhancement method includes:

[0057] Step S510: When the satellite device is relatively close to the space target and is about to perform imaging enhancement, the satellite device obtains angle information of the space target obtained by the laser radar imaging device. The angle information includes the angle θ between the normal line of the space target imaging surface and the central axis of the solar wing.

[0058] In step S520, based on the angle information, the posture adjustment mechanism and the deployment arm are controlled to point the central axis of the back side of the target solar wing of the satellite device toward the space target, so as to guide the mirror reflection film attached to the back side of the target solar wing to reflect sunlight onto the observation surface of the space target.

[0059] It should be understood that the specific process of controlling the posture adjustment mechanism and the deployment arm to point the central axis of the back of the target solar wing of the satellite device toward the space target based on the angle information can be set according to actual needs, and the embodiments of the present application are not limited to this.

[0060] Specifically, the imaging incremental guidance unit controls the LiDAR imaging device to acquire angle information of the space target. Based on this angle information, the unit controls the position adjustment mechanism and deployment arm to roughly align the central axis of the back of the target solar wing toward the space target, before the satellite device enters the fine-tuning range. Furthermore, based on the position feedback of the deployment arm and the angle information of the space target acquired by the LiDAR imaging device, the unit determines whether the satellite device has entered the fine-tuning range. If the satellite device is determined not to be within the fine-tuning range, the unit returns to controlling the position adjustment mechanism and deployment arm to roughly align the central axis of the back of the target solar wing toward the space target based on the angle information. If the satellite device is determined to be within the fine-tuning range, the unit controls the position adjustment mechanism and deployment arm to precisely align the central axis of the back of the target solar wing toward the space target.

[0061] It should be noted here that coarse pointing means that the angle θ between the normal of the space target imaging surface and the central axis of the solar wing is greater than or equal to 15° and less than or equal to 40°.

[0062] In addition, the specific process of determining whether the satellite device has entered the fine-tuning range based on the position feedback of the deployment arm and the angle information of the space target obtained by the lidar imaging device can be set according to actual needs, and the embodiments of the present application are not limited to this.

[0063] For example, when the angle θ between the normal of the imaging surface of the space target and the central axis of the solar wing is less than or equal to 15°, precise pointing adjustment begins, and the adjustment range of precise pointing is that the angle θ is greater than or equal to 0° and less than or equal to 15°, and when the distance between the satellite and the space target is less than or equal to 25km, imaging enhancement is implemented.

[0064] It should be understood that controlling the posture adjustment mechanism and the deployment arm will target

[0065] The specific process of accurately pointing the central axis of the back of the solar wing to the space target can be set according to actual needs, and the embodiments of the present application are not limited to this.

[0066] For example, the imaging incremental guidance unit controls the posture adjustment mechanism and the deployment arm to accurately point the central axis of the back of the target solar wing toward the space target, and obtains displacement data collected by the displacement sensor of the satellite device (or the position detection device performs position feedback through the displacement sensor, and the feedback position can be the spatial distance between the satellite and the target to be measured), and determines whether precise pointing has been achieved based on the displacement data and the angle information of the space target obtained by the laser radar imaging device. If precise pointing is not achieved, the process returns to the step of controlling the posture adjustment mechanism and the deployment arm to accurately point the central axis of the back of the target solar wing toward the space target; if precise pointing is achieved, the laser radar imaging device is controlled to observe and image the space target.

[0067] It should be noted here that imaging enhancement begins when the satellite approaches the space target within 25km. The coarse pointing adjustment range is 15°≤θ≤40°, and the fine pointing adjustment range is 0°≤θ≤15°. Ideally, the angle θ between the normal of the space target imaging surface and the central axis of the solar wing is 0°, at which time the imaging enhancement effect is the best.

[0068] Step S530: After accurately pointing to the space target, control the laser radar imaging device to observe and image the space target.

[0069] In step S540, the satellite device determines whether the imaging enhancement task is completed based on the ground-based information or the set duration. For example, the satellite device may determine that the imaging enhancement task is completed when it determines that the set duration has arrived.

[0070] If it is determined that the imaging enhancement task is completed, step S550 is executed; if it is determined that the imaging enhancement task is not completed, step S560 is executed.

[0071] In step S550 , the imaging enhancement guidance unit may control the deployment arm to restore the target solar wing to a normal position.

[0072] Step S560, waiting for ground mission instructions.

[0073] Therefore, the embodiment of the present application utilizes an imaging enhancement guidance unit to control the lidar imaging device to obtain precise angle information of the space target, and controls the deployment arm and the posture adjustment mechanism according to the measurement results to point the central axis of the solar wing reflective surface toward the geometric center of the target, guiding the mirror reflective film to reflect sunlight to the space target body, increasing the one-dimensional illumination direction, thereby forming better imaging illumination conditions to achieve the effect of imaging enhancement.

[0074] It should be understood that the above-mentioned space-based optical imaging enhancement method for space targets is merely exemplary, and those skilled in the art may make various modifications based on the above-mentioned method, and the modified schemes also fall within the scope of protection of this application.

[0075] Those skilled in the art will appreciate that embodiments of the present invention may be provided as methods, systems, or computer program products. Thus, the present invention may take the form of an entirely hardware embodiment, an entirely software embodiment, or an embodiment combining software and hardware aspects. Furthermore, the present invention may take the form of a computer program product implemented on one or more computer-usable storage media (including but not limited to magnetic disk storage, CD-ROM, optical storage, etc.) containing computer-usable program code.

[0076] The present invention is described with reference to flowcharts and / or block diagrams of methods, apparatus (systems), and computer program products according to embodiments of the invention. It should be understood that each process and / or block in the flowcharts and / or block diagrams, as well as combinations of processes and / or blocks in the flowcharts and / or block diagrams, can be implemented by computer program instructions.

[0077] It should be noted that, in the claims, any reference signs placed between brackets shall not be construed as limiting the claims. The word "comprising" does not exclude the presence of components or steps not listed in the claims. The word "a" or "an" preceding a component does not exclude the presence of a plurality of such components. The invention may be implemented by means of hardware comprising several different components and by means of a suitably programmed computer. In claims enumerating several means, several of these means may be embodied by one and the same hardware. The use of the words first, second, third etc. is for convenience only and does not indicate any order. These words may be understood as part of the component name.

[0078] In addition, it should be noted that, in the description of this specification, the description of the terms "one embodiment", "some embodiments", "embodiment", "example", "specific example" or "some examples" means that the specific features, structures, materials or characteristics described in conjunction with the embodiment or example are included in at least one embodiment or example of the present invention. In this specification, the schematic expressions of the above terms do not necessarily refer to the same embodiment or example. Moreover, the specific features, structures, materials or characteristics described can be combined in any one or more embodiments or examples in a suitable manner. In addition, those skilled in the art can combine and combine different embodiments or examples described in this specification and the features of different embodiments or examples, unless they are contradictory.

[0079] Although the preferred embodiments of the present invention have been described, those skilled in the art may make additional changes and modifications to these embodiments after learning the basic creative concept. Therefore, the claims should be interpreted as including the preferred embodiments and all changes and modifications that fall within the scope of the present invention.

[0080] Obviously, those skilled in the art may make various modifications and variations to the present invention without departing from the spirit and scope of the present invention. Thus, if such modifications and variations fall within the scope of the claims and their equivalents, the present invention shall also include such modifications and variations.

Claims

1. A satellite device, characterized in that: include: cabin; a target solar wing, wherein the target solar wing is connected to a posture adjustment mechanism fixed to the cabin through a corresponding deployment arm, a mirror reflective film is affixed to the back of the target solar wing, and a laser radar imaging device is also installed on the target solar wing; An imaging enhancement guidance unit is encapsulated in a system management unit of a satellite integrated electronic subsystem. The imaging enhancement guidance unit is used to control the deployment arm and the posture adjustment mechanism to point the central axis of the back of the target solar wing toward the space target based on the angle information of the space target obtained by the laser radar imaging device, so as to guide the mirror reflection film to reflect sunlight onto the observation surface of the space target, and to control the laser radar imaging device to observe and image the space target.

2. The satellite device according to claim 1, wherein: The mirror reflection film includes a substrate, a transition layer arranged on the substrate, a reflection layer arranged on the transition layer, and a protection layer arranged on the reflection layer.

3. The satellite device according to claim 2, wherein: The thickness of the substrate is 98-102 μm, the thickness of the transition layer is 0.02-0.04 μm, the thickness of the reflective layer is 0.1-0.2 μm, and the thickness of the protective layer is 4-6 μm.

4. The satellite device according to claim 2 or 3, characterized in that: The material of the substrate is polyimide or ultra-thin glass, the material of the transition layer is Cr or aluminum oxide, the material of the reflective layer is Ag, and the material of the protective layer is silicon dioxide.

5. The satellite device according to claim 1, wherein: The deployment arm includes a base joint, an elbow joint, and a wrist joint.

6. A space-based optical imaging enhancement method for space targets, characterized in that: The space-based optical imaging enhancement method is applied to the imaging enhancement guidance unit of the satellite device according to any one of claims 1 to 5; The space-based optical imaging enhancement method comprises: Acquiring angle information of a space target acquired by a laser radar imaging device of the satellite device; controlling, based on the angle information, a position adjustment mechanism and a deployment arm of the satellite device to direct a central axis of a back surface of a target solar wing of the satellite device toward the space target, thereby guiding a mirror reflective film attached to the back surface of the target solar wing to reflect sunlight onto an observation surface of the space target; Control the laser radar imaging device to observe and image the space target.

7. The space-based optical imaging enhancement method according to claim 6, characterized in that: The step of controlling the attitude adjustment mechanism and the deployment arm of the satellite device to direct the central axis of the back side of the target solar wing of the satellite device toward the space target based on the angle information includes: Before the satellite device enters the fine adjustment range, controlling the posture adjustment mechanism and the deployment arm according to the angle information to roughly point the central axis of the back side of the target solar wing toward the space target; determining whether the satellite device has entered the fine adjustment range based on position feedback of the deployment arm and angle information of the space target acquired by the laser radar imaging device; If it is determined that the satellite device has entered the fine adjustment range, the posture adjustment mechanism and the deployment arm are controlled to accurately point the central axis of the back of the target solar wing to the space target.

8. The space-based optical imaging enhancement method according to claim 7, characterized in that: The controlling the posture adjustment mechanism and the deployment arm to accurately point the central axis of the back side of the target solar wing toward the space target comprises: acquiring displacement data collected by a displacement sensor of the satellite device; determining whether precise pointing has been achieved based on the displacement data and the angle information of the space target acquired by the laser radar imaging device; If precise pointing is not achieved, continue to control the posture adjustment mechanism and the deployment arm to accurately point the central axis of the back of the target solar wing toward the space target until precise pointing is achieved.

9. The space-based optical imaging enhancement method according to claim 6, characterized in that: Before controlling the attitude adjustment mechanism and the deployment arm of the satellite device to direct the central axis of the back surface of the target solar wing of the satellite device toward the space target based on the angle information, the space-based optical imaging enhancement method further includes: Acquiring jitter information of the surface of the target solar wing; According to the jitter information, the stabilization control mechanism of the satellite device is controlled to correct the direction of the solar wing surface.

Images