Machine Vision-Supported Inter-Satellite Link Acquisition

Abstract

The present invention provides a method and apparatus for reducing the uncertainty field of the estimation of the satellite position in a constricted space. This reduction of the uncertainty field estimation shortens the link acquisition time when satellites establish inter-satellite optical links with each other. The method and apparatus reduce the above-mentioned estimated uncertainty field by combining the estimated uncertainty fields generated by multiple independent sources. The method further includes combining the estimated uncertainty field generated using existing uncertainty field techniques with the estimated uncertainty field created by a machine vision detection and positioning module. Such a machine vision detection and positioning module generates an estimated uncertainty field, which is the result of performing one or more algorithms to process digital image data provided by a passive digital camera.

Description

[0001] Cross - Reference to Related Applications

[0002] This application claims priority to U.S. Non - Provisional Patent Application No. 16 / 908,993, filed on June 23, 2020, entitled "Inter - Satellite Link Acquisition Supported by Machine Vision". Technical Field

[0003] The present invention relates to satellite - based networks, such as optical satellite mesh networks, and in particular, to methods and apparatuses for supporting inter - satellite link acquisition operations. Background Art

[0004] Low Earth Orbit (LEO) satellite constellations are being developed to provide Internet routing services and the like. Currently, a group of satellites are proposed to be distributed in space and organized into a mesh network. Free - space optical (i.e., laser) links are proposed as a way to provide high - bandwidth network connections between satellites. Other types of links, such as radio frequency or microwave links, can also be used. One of the technical problems with LEO constellations is that due to the relative motion of the satellites in the constellation, inter - satellite links periodically experience signal loss. For example, this occurs when satellite orbits intersect (e.g., at or near the poles) and the east - west links are switched. Other examples occur at the seams and east - west links of constellations with orbits deviating from the poles. A seam, for example, refers to a boundary where on one side of the boundary are satellites in one of two counter - rotating hemispheres or spheres, and on the other side of the boundary are satellites in the other of the two counter - rotating hemispheres or spheres. Communication links between satellites in different hemispheres of the two counter - rotating hemispheres intersect the seam or sphere.

[0005] Re - acquiring a satellite link after such a loss can be a time - consuming process. Current optical link acquisition times are estimated to range from 10 to 60 seconds, with a relatively low success rate of 99%. Most of this link acquisition time is due to the need for spatial acquisition operations in which the communication lasers on adjacent satellites are correctly aimed at the corresponding receivers. Link acquisition may involve complex scan / stare patterns to allow each satellite to acquire the link by mechanically pointing the communication laser at the target satellite. Techniques for improving link acquisition time are desirable because the link cannot be used to send data until the link acquisition is complete.

[0006] Passive optical camera technology has matured to the point where small, reliable, and high - quality passive digital cameras are readily available. In recent years, machine vision technology has also advanced significantly, for example, through deep learning to facilitate object recognition.

[0007] Because the link acquisition time is relatively long, link interruption can affect network operation. Therefore, methods and apparatuses for shortening the link acquisition time are needed.

[0008] This background information is provided to disclose information that the applicant believes may be relevant to the present invention. It is not necessary to admit and should not be construed that any of the foregoing information constitutes prior art relative to the present invention. Summary of the Invention

[0009] An object of embodiments of the present invention is to provide a method and apparatus for supporting inter-satellite link acquisition operations using machine vision, which refers to automatically processing optical signals from a passive digital camera.

[0010] According to an embodiment of the present invention, a method for supporting an inter-satellite communication link acquisition operation is provided. The method includes using a passive digital camera to facilitate link acquisition. The method includes: generating digital image data using a passive digital camera, the digital image data representing one or more optical images of a spatial region that may contain a target satellite. The method further includes: processing the digital image data using a processor to reduce an uncertainty field. The uncertainty field is a subset of the spatial region where the target satellite is expected to be located.

[0011] In some embodiments, the spatial region is selected to coincide with the region pointed to by a communication laser beam, or to coincide with the region pointed to by an optical receiver for receiving communication signals. In some other embodiments, the communication laser is aligned with the passive digital camera, in which case the method further includes guiding the communication laser to point to the target satellite after the target satellite is located.

[0012] In some other or any of the above embodiments, the optical image is generated based on light provided to the passive digital camera through a set of optical elements, and the set of optical elements is also configured to guide a communication laser beam transmitted toward the target satellite, a communication laser beam received from the target satellite, or both. In some other or any of the above embodiments, reducing the uncertainty field includes identifying one or more of the following: the position of the target satellite; the identification of the target satellite; and the position of a communication transmitter or receiver on the target satellite. One or more of the position of the target satellite, the identification of the target satellite, and the position of the communication transmitter can be determined using a unique visual indication associated with the target satellite. In some other or any of the above embodiments, reducing the uncertainty field includes identifying the position of the target satellite, and in these embodiments, the method further includes: based on the position of the target satellite, adjusting the optical elements of the satellite to guide a communication laser beam transmitted toward the target satellite, guide a communication laser beam received from the target satellite, or both.

[0013] According to an embodiment of the present invention, a satellite device is provided. The satellite device has a passive digital camera, a processor, and at least one of an optical transmitter and an optical receiver. The passive digital camera is configured to generate digital image information representing one or more optical images of a spatial region that may contain a target satellite. The processor is configured to receive the generated digital image information and process the received digital images to narrow an uncertainty field, which is a subset of the spatial region where the target satellite is expected to be located.

[0014] In some embodiments, the processing of the uncertainty field estimation is performed using a trained neural network. The trained neural network may include a deep learning network. The estimation of the uncertainty field may include information indicating one or more of the following: the position of the target satellite; the identity of the target satellite; the position of the communication transmitter of the target satellite; the position of the communication receiver of the target satellite. In some other or any of the above embodiments, one or more of the position of the target satellite, the identity of the target satellite, the position of the communication transmitter of the target satellite, and the position of the communication receiver of the target satellite are determined by the processor using a unique visual indication associated with the target satellite. The unique visual indication associated with the target satellite may include one or more of the following: a unique visual marker; a unique illumination; a unique reflection from the target satellite.

[0015] In some other or any of the above embodiments, the passive digital camera generates digital image data representing the uncertainty field coaxial with the telescope. The digital image data may represent an estimated uncertainty field that may contain the target satellite. In some other or any of the above embodiments, the spatial region coincides with the region pointed to by a communication laser beam or with the region pointed to by an optical receiver for receiving communication signals. The communication laser may also be aligned with the passive digital camera. In these embodiments, the device is further configured to: after the target satellite is located, direct the communication laser towards the target satellite.

[0016] In some other or any of the above embodiments, the one or more optical images are generated based on light provided to the passive digital camera by a set of optical elements, which are also configured to direct a communication laser beam transmitted towards the target satellite, a communication laser beam received from the target satellite, or both. In some other or any of the above embodiments, reducing the uncertainty field includes identifying one or more of the following: the position of the target satellite; the identity of the target satellite; and the position of a communication transmitter or receiver on the target satellite. In some other or any of the above embodiments, one or more of the position of the target satellite, the identity of the target satellite, and the position of the communication transmitter are determined using a unique visual indication associated with the target satellite. In some other or any of the above embodiments, reducing the uncertainty field includes identifying the position of the target satellite, and in these embodiments, the apparatus is further configured to: based on the position of the target satellite, adjust the optical elements of the satellite to direct a communication laser beam transmitted towards the target satellite, direct a communication laser beam received from the target satellite, or both.

[0017] Embodiments have been described above in connection with aspects of the present invention, and these embodiments may be implemented based on these aspects. Those skilled in the art will understand that embodiments may be implemented in combination with the aspects that describe them, but may also be implemented with other embodiments of that aspect. When embodiments are mutually exclusive or incompatible with each other, this will be apparent to those skilled in the art. Some embodiments may be described in connection with one aspect, but may also be applicable to other aspects, which is apparent to those skilled in the art. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Further features and advantages of the present invention will become apparent from the following detailed description when taken in conjunction with the accompanying drawings.

[0019] Figure 1 An example of a satellite network integrated with a terrestrial network according to an embodiment of the present invention is shown.

[0020] Figure 2 An example of four satellites orbiting the Earth along an orbit and communicating via an inter-satellite optical link according to an embodiment of the present invention is shown.

[0021] Figure 3 An example of an uncertainty field region and an associated spiral scan trajectory according to an embodiment of the present invention is shown.

[0022] Figure 4 An embodiment of the present invention having a machine vision detection and positioning module is shown.

[0023] Figure 5A method for estimating an uncertainty field according to an embodiment of the present invention is shown.

[0024] Figure 6 An electronic device according to an embodiment of the present invention is shown schematically.

[0025] It should be noted that in all the drawings, the same features are identified by the same reference numerals. Detailed implementation manners

[0026] As used herein, the term "about" should be understood to include variations relative to the nominal value, e.g., a + / - 10% variation relative to the nominal value. It should be understood that the given values provided herein always include such variations whether or not specifically mentioned.

[0027] Figure 1 An example of a satellite network integrated with a terrestrial network is shown. Referring Figure 1 , a satellite network 100 integrated with a terrestrial network is provided. The satellite network 100 includes low earth orbit (LEO) satellites 110 and 120 in a satellite constellation. The LEO satellites 110 and 120 may be placed in different orbits. The LEO satellites 110 and 120 may communicate using inter-satellite optical links. The LEO satellites 110 and 120 are connected to terrestrial user terminals. Optical fibers 135 and a wireless network 130 are interconnected with the satellites through a gateway 140 to form a global heterogeneous network. Based on Figure 1 The data network based on the LEO constellation topology shown in can provide data network services, especially in areas with poor or congested terrestrial infrastructure deployments.

[0028] Figure 2 Four LEO satellites 210, 220, 230, and 240 are shown. Each of the satellites 210, 220, 230, and 240 may communicate with another satellite using an inter-satellite optical link 250. Each of the satellites 210, 220, 230, and 240 includes a communication laser that may perform an optical transmitter function. Each of the satellites 210, 220, 230, and 240 also includes an associated optical transmitter and an optical receiver (not shown). The satellite that sends information is referred to as the first satellite, and the satellite that receives information is referred to as the target satellite. Those skilled in the art will understand that although the discussion is directed to optical links, other focused RF links may be employed in other embodiments.

[0029] Establishing an inter-satellite optical link 250 using a conventional link acquisition process is generally a relatively slow process. This slow acquisition process involves a first satellite directing its communication laser to the optical receiver of a target satellite, while the target satellite directs its communication laser to the optical receiver of the first satellite. The communication laser of the first satellite must be precisely aligned with the optical receiver on the target satellite. Since this is typically a blind alignment, it is a technical challenge. The first satellite and the target satellite direct their communication lasers through a spatial region where each satellite predicts that the position of the other satellite will be located within this spatial region. This spatial region is known to those skilled in the art as the uncertainty field. The uncertainty field is typically calculated using an open-loop process based on satellite ephemeris data. The first satellite and the target satellite, and thus these two narrow-beam communication lasers, may be hundreds of kilometers apart. According to traditional literature and modeling, this slow acquisition process takes 10 to 60 seconds to complete, and the target success rate of this acquisition process is 99%.

[0030] According to various embodiments, the slow acquisition process includes multiple stages: coarse space, fine space, and frequency. The coarse space stage consumes the most time among these three stages.

[0031] The coarse space acquisition stage involves a combination of a scanning pattern and independent scan / stare cooperation. Independent scans can include raster scans, spiral scans, Lissajous scans, or combinations thereof.

[0032] Figure 3 The uncertainty field 310 and the associated spiral scan trajectory 320 are shown. Searching for the target satellite is performed by acquiring information for each of a plurality of individual angular scan positions represented by positions along the spiral scan trajectory 320. The larger the uncertainty field 310, the more steps are generally required to search for the target satellite. It should be understood that reducing the uncertainty field, for example, using the information obtained by the machine vision system disclosed herein, can have the effect of reducing the size of the uncertainty field. This will have the effect of shortening the time required to complete the spiral scan trajectory, and thus shortening the time required to complete the above-mentioned slow acquisition process.

[0033] Those skilled in the art will understand that by combining information from multiple independent sources, the estimation of the target satellite position can be improved, and the size of the uncertainty field can be reduced. For example, the information obtained from machine vision processing techniques can be combined with other information (such as satellite ephemeris data) to estimate the target satellite position within a more limited uncertainty field. Reducing the uncertainty field helps the satellite link acquisition operation by reducing the spatial region searched for the position of the target satellite, the identity of the target satellite, and the position of the communication laser or receiver of the target satellite.

[0034] Embodiments of the present invention can supplement existing link acquisition techniques, such as guiding an optical receiver into an uncertainty field to receive communication signals.

[0035] In some embodiments, the communication laser of the first satellite is guided to the optical receiver of a single target satellite, and the optical receiver of the first satellite receives a laser beam from the communication laser of the single target satellite. In other embodiments, the communication laser of the first satellite is guided to the optical receivers of more than one target satellite, and the optical receiver of the first satellite receives multiple laser beams from multiple target satellites.

[0036] Embodiments of the present invention can be used to guide the communication laser of a satellite, including guiding the light beam of the communication laser after the communication laser is emitted. The light beam of the communication laser can be guided by adjusting the optical elements of the satellite to direct the communication laser beam towards a target satellite. Embodiments can adjust the optical elements of the satellite to guide (within the internal optics of the first satellite) the communication laser beam received from a target satellite. Embodiments can adjust the optical elements to direct the communication laser beam towards a target satellite, to guide the communication laser beam received from a target satellite, or a combination thereof.

[0037] The present invention uses a machine vision system to identify a target satellite orbiting in space. Since the target satellite may not be in the exact position indicated by an almanac or other such data source (either in absolute terms or relative to the first satellite), identifying the position of the target satellite can allow the first satellite to reduce the size of the search space associated with the rough position during the first stage of link acquisition. The first satellite can use information obtained from a passive (usually digital) camera pointed at the expected position of the target satellite. A passive camera is a device that does not transmit its own light to reflect the target object, but relies on detecting other (e.g., ambient) light emitted or reflected by the target object. A passive digital camera can refer to a device that converts an optical image into a digital image indicating the light emitted from a given area. A passive digital camera can use a light sensor (such as a charge-coupled device, or complementary metal-oxide-semiconductor sensor) that provides an electrical signal output, which is typically digitized (discretized) and interpreted using electronic devices. The first satellite can include a communication laser for transmitting signals to the target satellite, and the target satellite can include a communication laser for transmitting signals to the first satellite. The target satellite may or may not include a passive digital camera. The passive digital camera of the first satellite is typically aligned with the communication laser of the first satellite. The alignment allows the camera to acquire an image of the spatial area pointed at by the communication laser. The target satellite can be similarly equipped.

[0038] Embodiments of the present invention can use the same optical elements that guide the communication laser beam, thus also providing an optical image to the passive digital camera. Therefore, the passive digital camera and one or more communication lasers can share a common optical component. For example, the communication laser and the light to be collected by the camera can pass through the same telescope element and optical elements, such as a beam splitter or a mirror. The communication laser and the light to be collected by the camera can be split in different directions within the optical component of the satellite at a given point.

[0039] Alternative embodiments can use a first set of optical elements to guide the communication laser beam and a second separate set of optical elements to process the light to be collected by the camera.

[0040] As the first satellite moves in its orbit, the first satellite can use a passive digital camera and associated machine vision techniques that operate on the digital images output from the passive digital camera to collect some images. These images can be processed by a machine vision processor to identify different visual indicators that can be used to identify the position of the target satellite. The visual indicators can include a visual image of the target satellite. The visual indicators can include unique markings located on the target satellite. The visual indicators can also include unique illumination used by the target satellite, such as a specific pattern of light emitters or reflectors. These visual indicators can be used to supplement other information indicating the predicted position of the target satellite. This information from the machine vision system can be combined with other information to identify, locate, or identify and locate the target satellite or its communication laser or its receiver system.

[0041] The machine vision system can operate based on one or more machine vision techniques. Examples of applicable machine vision techniques include Histogram of Oriented Gradients, Hough transform, Scale-Invariant Feature Transform (SIFT), and trained neural networks, including deep learning neural networks. The machine vision system can be used to automatically detect objects in the image, such as the target satellite or transmitters or receivers located thereon, or other contextual objects indicating the position of the target satellite, such as background objects. The machine vision system can be used to distinguish the target satellite from other objects, such as non-target satellites. These techniques can be based on pre-programmed rules, machine learning, or a combination thereof.

[0042] Multiple machine vision techniques are often combined to provide a more efficient solution. For example, an application can use edge detection to identify object features and then use SIFT or the Hough transform to assemble the identified features into an object.

[0043] The target satellite in embodiments of the present invention can also utilize a passive digital camera and a machine vision system to determine the predicted position of the first satellite.

[0044] In various embodiments, the passive digital camera and the communication laser of the first satellite are sufficiently aligned such that after the target satellite is located using at least in part the digital image provided by the passive digital camera, the communication laser can be quickly and accurately directed to the receiver location on the target satellite. For example, the communication laser can be directed to an area that is also substantially at the center of the digital camera image. Thus, maintaining sufficient alignment between the passive digital camera and the communication laser reduces the time required for the first satellite to acquire the target satellite in space.

[0045] Reference Figure 4 , the telescope 415 is directed at a spatial region that may contain the target satellite. This spatial region contains an uncertainty field known to those skilled in the art. Light 410 including an image of the uncertainty field enters the telescope 415. Then, the telescope 415 outputs an image of the estimated uncertainty field 420 to the fine steering mirror 425. The fine steering mirror 425 corrects the distortion included in the image of the estimated uncertainty field 420 to produce an image 430. Then, the image 430 impinges on a beam splitter 435, which produces an image 440 and an image 460. The image 440 is applied to the machine vision detection and positioning module 445. The machine vision detection and positioning module 445 processes digital images. The digital image can be produced by a passive digital camera (not shown), where the passive digital camera produces one or more digital images from the image 440. The passive digital camera can be included in the machine vision detection and positioning module 445. The digital image produced by the passive digital camera is coaxial with the optical communication device because the optical communication beam associated with the optical communication device passes through a common axis and the light is collected by the digital camera. The machine vision detection and positioning module 445 processes the digital image produced by the passive digital camera based on machine vision techniques to produce an estimated uncertainty field 450, estimate the position, identity, and orientation of the target satellite, or a combination thereof.

[0046] In some embodiments, the machine vision detection and positioning module 445 processes the digital image produced by the passive digital camera using a deep neural network and techniques including histogram of oriented gradients, scale-invariant feature transform, and speeded-up robust feature detection.

[0047] The image 460 impinges on a beam splitter 465 to produce an image 470. The acquisition / tracking detector 485 processes the image 470 and the signal 480 produced by the receiver 475 to produce a signal 490.

[0048] The estimator and controller 455 combines the estimated uncertainty field 450 with the signal 490 generated by the acquisition / tracking detector 485 to improve the uncertainty field estimation and acquire the communication laser link faster. For example, the estimator and controller 455 can adjust the target scan pattern or scan area (uncertainty field) based on information from the machine vision detection and positioning module 445, at least in part by combining ephemeris data and calculations. In some embodiments, the signal transmitted by the transmitter to the target satellite is within a wavelength range that can be detected by a passive camera. This will allow the machine vision detection and positioning module 445 to determine when the signal from the transmitter hits the target satellite but not the receiver. The estimation controller 455 can use this information to assist in aiming the communication signal transmitted to the target satellite.

[0049] In an alternative embodiment of the present invention, the passive digital camera can be a separate component of the communication laser system and can use independent optics. The independent optics can include a second telescope, separate optical elements, or a combination thereof. The digital images generated by the passive digital camera are processed by the machine vision detection and positioning module 445 to generate the estimated uncertainty field 450.

[0050] Figure 5 A method for estimating a spatial region that may contain a target satellite, which is an uncertainty field known to those skilled in the art, according to an embodiment of the present invention is shown. Figure 5 The method shown can be executed by a machine vision detection and positioning module within one or more satellites in a satellite constellation. Referring Figure 5 , an embodiment of the present invention includes a passive digital camera associated with a satellite. Such a passive digital camera generates digital image data. The digital image data represents one or more optical images to estimate an uncertainty field that may contain the target satellite 510. The image is generated coaxially with the optical image generated by a telescope on the same satellite. The machine vision detection and positioning module of the present invention processes 520 the digital image data based on machine vision techniques. This can include identifying objects in the digital image, such as the target satellite or associated reference objects. The machine vision positioning and detection module also generates 530 an improved estimate of the uncertainty field. This can include estimating the uncertainty field to be further analyzed to locate the target satellite. This can include identifying the target satellite within the uncertainty field.

[0051] Figure 6 is a schematic diagram of an electronic device 600 according to different embodiments of the present invention. The electronic device 600 can perform any or all of the operations of the above-described methods and features explicitly or implicitly described herein. For example, a computer equipped with network capabilities can be configured as the electronic device 600.

[0052] As shown in the figure, the device includes a processor 610 such as a central processing unit (CPU) or a dedicated processor (such as a graphics processing unit (GPU) or other such processor unit), a memory 620, a non-transitory mass storage 630, an I / O interface 640, a network interface 650, and a transceiver 660, all of which are communicatively coupled via a bidirectional bus 670. According to certain embodiments, any or all of the described elements may be used, or only a subset of these elements. Additionally, the device 600 may include multiple instances of certain elements, such as multiple processors, memories, or transceivers. Further, the elements of the hardware device may be directly coupled to other elements without a bidirectional bus. Additionally or alternatively, other electronic devices such as integrated circuits may be employed to perform the required logical operations in addition to the processor and the memory.

[0053] The memory 620 may include any type of non-transitory memory, such as static random access memory (SRAM), dynamic random access memory (DRAM), synchronous DRAM (SDRAM), read-only memory (ROM), or a combination thereof, etc. The mass storage element 630 may include any type of non-transitory storage device, such as a solid-state drive, a hard disk drive, a disk drive, an optical drive, a USB drive, or any computer program product configured to store data and machine-executable program code. According to certain embodiments, the memory 620 or the mass storage 630 may record statements and instructions executable by the processor 610 for performing any of the method operations described above.

[0054] The actions associated with the methods described herein may be implemented as encoded instructions in a computer program product. In other words, a computer program product is a computer-readable medium having software code recorded thereon, which, when loaded into the memory and executed on the microprocessor of a wireless communication device, performs the methods described above.

[0055] The actions associated with the methods described herein can be implemented as encoded instructions in multiple computer program products. For example, the first part of the method can be executed using one computing device, and the second part of the method can be executed using other computing devices, servers, etc. In such cases, each computer program product is a computer-readable medium having software code recorded thereon, which, when loaded into a memory and executed on a microprocessor of a computing device, executes the appropriate part of the above-described method.

[0056] In addition, each operation of the above-described method can be executed on any computing device (such as a personal computer, server, personal digital assistant (PDA), etc.) and is executed in accordance with one or more program elements, modules, or objects generated from any programming language (such as C++, Java, etc.) or a part of one or more program elements, modules, or objects. Additionally, each operation or the file or object, etc. implementing each of the above operations can be executed by dedicated hardware or a circuit module designed for that purpose.

[0057] From the description of the above embodiments, the present invention can be implemented only by using hardware, or can be implemented by software and a necessary general hardware platform. Based on such an understanding, the technical solution of the present invention can be embodied in the form of a software product. The software product can be stored in a non-volatile or non-transitory storage medium, and the non-volatile or non-transitory storage medium can be a compact disk read-only memory (CD-ROM), a USB flash drive, or a removable hard disk. The software product includes many instructions that enable a computer device (personal computer, server, or network device) to execute the methods provided in the embodiments of the present invention. For example, such execution can correspond to an emulation of the logical operations as described herein. The software product can additionally or alternatively include multiple instructions that enable a computer device to execute the operations of configuring or programming a digital logic device according to the embodiments of the present invention.

[0058] Although the present invention has been described with reference to specific features and embodiments of the present invention, it is obvious that various modifications and combinations of the present invention can be made without departing from the present invention. Therefore, the specification and the drawings are only to be regarded as an illustration of the present invention defined by the appended claims, and it is intended to cover any and all modifications, variations, combinations, or equivalents falling within the scope of the present invention.

Claims

1. A method for supporting the acquisition operation of an inter-satellite communication link, characterized in that, Comprising: Using a passive digital camera to generate digital image data, the digital image data representing one or more optical images of a spatial region potentially containing a target satellite; Using a processor to process the digital image data to reduce an uncertainty field, the uncertainty field being a subset of the spatial region where the target satellite is expected to be located; The one or more optical images are generated based on light provided to the passive digital camera through a set of optical elements, the set of optical elements also being configured to direct a communication laser beam transmitted towards the target satellite, a communication laser beam received from the target satellite, or both.

2. The method according to claim 1, wherein The spatial region is selected to coincide with the region towards which the communication laser beam is directed, or with the region towards which a light receiver is directed for receiving a communication signal.

3. The method according to claim 2, wherein The communication laser beam is aligned with the passive digital camera, and the method further includes, after the target satellite is located, directing the communication laser beam towards the target satellite.

4. The method according to any one of claims 1 to 3, characterized in that, Reducing the uncertainty field includes identifying one or more of the following: the position of the target satellite; the identification of the target satellite; and the position of a communication transmitter or receiver on the target satellite.

5. The method according to claim 4, characterized in that One or more of the position of the target satellite, the identification of the target satellite, and the position of the communication transmitter are determined using a unique visual indication associated with the target satellite.

6. The method according to any one of claims 1 to 3, characterized in that Reducing the uncertainty field includes identifying the position of the target satellite, and the method further includes: based on the position of the target satellite, adjusting the optical elements of the target satellite to direct a communication laser beam transmitted towards the target satellite, direct a communication laser beam received from the target satellite, or both.

7. A satellite device, characterized in that, Comprising: A passive digital camera configured to generate digital image information, the digital image information representing one or more optical images of a spatial region potentially containing a target satellite; A processor configured to receive the generated digital image information and process the received digital image information to reduce an uncertainty field, the uncertainty field being a subset of the spatial region where the target satellite is expected to be located; And At least one of a light transmitter and a light receiver; The one or more optical images are generated based on light provided to the passive digital camera through a set of optical elements, the set of optical elements also being configured to direct a communication laser beam transmitted towards the target satellite, a communication laser beam received from the target satellite, or both.

8. The device according to claim 7, wherein The estimation of processing the uncertainty field is performed using a trained neural network.

9. The device according to claim 8, characterized in that, The trained neural network includes a deep learning network.

10. The device according to any one of claims 7 to 9, characterized in that The light receiver receives light from one of the following: The communication laser of a single target satellite; The communication lasers of multiple target satellites.

11. The device according to claim 8 or 9, characterized in that, The estimation of the uncertainty field includes information indicating one or more of the following: The position of the target satellite; The identification of the target satellite; The position of the communication transmitter of the target satellite; The position of the communication receiver of the target satellite.

12. The device according to claim 11, characterized in that, One or more of the location of the target satellite, the identification of the target satellite, the location of the communication transmitter of the target satellite, and the location of the communication receiver of the target satellite are determined by the processor using a unique visual indication associated with the target satellite.

13. The device according to claim 12, characterized in that, The unique visual indication associated with the target satellite includes: A unique visual marker; Unique illumination; A unique reflection from the target satellite.

14. The device according to any one of claims 7 to 9, characterized in that, The passive digital camera generates digital image data representing the field of uncertainty coaxial with the telescope.

15. The device according to claim 14, characterized in that, The digital image data represents an estimated field of uncertainty that potentially contains the target satellite.

16. The device according to any one of claims 7 to 9, characterized in that, The spatial region coincides with the region to which the communication laser beam is directed, or with the region to which the optical receiver is directed for receiving communication signals.

17. The device according to claim 16, wherein The communication laser beam is aligned with the passive digital camera, and the apparatus is further configured to, after the target satellite is located, direct the communication laser beam towards the target satellite.

18. The device according to any one of claims 7 to 9, characterized in that Narrowing the field of uncertainty includes identifying one or more of: the location of the target satellite; the identification of the target satellite; and the location of the communication transmitter or receiver on the target satellite.

19. The device according to claim 18, characterized in that, One or more of the location of the target satellite, the identification of the target satellite, and the location of the communication transmitter are determined using a unique visual indication associated with the target satellite.

20. The device according to any one of claims 7 to 9, characterized in that, Narrowing the field of uncertainty includes identifying the location of the target satellite, and the apparatus is further configured to: based on the location of the target satellite, adjust the optical elements of the target satellite to direct a communication laser beam transmitted towards the target satellite, direct a communication laser beam received from the target satellite, or both.

Images