Artificial satellite with multiple sensors

Abstract

The present invention is directed to an artificial satellite with multiple sensors mounted through at least one gimbal. The artificial satellite is operable to support an RGB video telescope, a hyperspectral sensor, an ultraviolet instrument, an infrared spectrometer, and / or at least one AIS receiver. The artificial satellite includes a power system that enables it to support a multitude of sensors. The multiple sensors are configured to capture and compile image data from a single target.

Description

Attorney Docket No.4604-002PCT ARTIFICIAL SATELLITE WITH MULTIPLE SENSORS CROSS-REFERENCE TO RELATED APPLICATIONS

[0001] This application is related to and claims priority from the following US patents and patent applications: this application claims priority from and the benefit of U.S. Patent Application No.19 / 057,488, filed February 19, 2025, and U.S. Provisional Patent Application No.63 / 564,275, filed March 12, 2024. U.S. Patent Application No.19 / 057,488 also claims priority from and the benefit of U.S. Provisional Patent Application No.63 / 564,275, filed March 12, 2024. Each of the above applications is incorporated herein by reference in its entirety. BACKGROUND OF THE INVENTION

[0002] 1. Field of the Invention

[0003] The present invention relates to an artificial satellite having more than one sensor, and more specifically to individual artificial satellites including optical sensors, hyperspectral sensors, video generators, and ultraviolet sensors.

[0004] 2. Description of the Prior Art

[0005] It is generally known in the prior art to provide to provide an artificial satellite with a sensor.

[0006] Prior art patent documents include the following:

[0007] US Patent No.10,496,883 for Method and system for enhancing predictive accuracy of planet surface characteristics from orbit by inventor Kwan, filed January 27, 2017 and issued December 3, 2019, discloses a method and system for enhancing predictive accuracy of planet surface characteristics from orbit using an extended approach of Pan-Sharpening by using multiple high resolution bands to reconstruct high resolution hyperspectral image. Sparsity based classification algorithm is applied to rock type classification. An Extended Yale B face database is used for performance evaluation; and utilizing deep Neural Networks for pixel classification. The present invention presents a system that can significantly enhance the predictive accuracy of surface characteristics from the orbit. The system utilizes complementary images collected from imagers onboard satellites. The present system and method generates high spatial high spectral resolution images; accurate detection of anomalous regions on Mars, Earth, or other planet surfaces; accurate rock / material classification using orbital data and the surface characterization performance will be comparable to in-situ results; and accurate chemical concentration estimation of rocks.

[0008] US Patent Publication No.2003 / 0095181 for Direct broadcast imaging satellite system apparatus and method for providing real-time, continuous monitoring of earth from geostationary earth orbit by inventor LeCompte, filed November 20, 2002 and published May 22, 2003, discloses a system, method and apparatus for collecting an distributing real-time, highAttorney Docket No.4604-002PCT resolution images of the Earth from GEO include an electro-optical sensor based on multi- megapixel two-dimensional charge coupled device (CCD) arrays mounted on a geostationary platform. At least four, three-axis stabilized satellites in Geostationary Earth orbit (GEO) provide worldwide coverage, excluding the poles. Image data that is collected at approximately 1 frame / sec, is broadcast over high-capacity communication links (roughly 15 MHZ bandwidth) providing real-time global coverage of the Earth at sub-kilometer resolutions directly to end users. This data may be distributed globally from each satellite through a system of space and ground telecommunication links. Each satellite carries at least two electro-optical imaging systems that operate at visible wavelengths so as to provide uninterrupted views of the Earth's full disk and coverage at sub-kilometer spatial resolutions of most or selected portions of the Earth's surface.

[0009] US Patent Publication No.2018 / 0167586 for Satellite imaging system with edge processing by inventors Rutschman et. al., filed December 15, 2017 and published June 14, 2018, discloses a satellite imaging system with edge processing includes, but is not limited to, at least one first imaging unit configured to capture and process imagery of a first field of view; at least one second imaging unit configured to capture and process imagery of a second field of view that is proximate to and larger than a size of the first field of view; and a hub processing unit linked to the at least one first imaging unit and the at least one second imaging unit.

[0010] US Patent Publication No.2002 / 0041328 for Direct broadcast imaging satellite system apparatus and method for providing real-time, continuous monitoring of earth from geostationary earth orbit and related services by inventors LeCompte et al., filed March 29, 2001 and published April 11, 2002, discloses a system, method and apparatus for collecting an distributing real-time, high resolution images of the Earth from GEO include an electro-optical sensor based on multi-megapixel two-dimensional charge coupled device (CCD) arrays mounted on a geostationary platform. At least four, three-axis stabilized satellites in Geostationary Earth orbit (GEO) provide worldwide coverage, excluding the poles. Image data that is collected at approximately 1 frame / sec, is broadcast over high-capacity communication links (roughly 15 MHz bandwidth) providing real-time global coverage of the Earth at sub-kilometer resolutions directly to end users. This data may be distributed globally from each satellite through a system of space and ground telecommunication links. Each satellite carries at least two electro-optical imaging systems that operate at visible wavelengths so as to provide uninterrupted views of the Earth's full disk and coverage at sub-kilometer spatial resolutions of most or selected portions of the Earth's surface.

[0011] US Patent No.10,647,449 for Indirect self-imaging systems and methods by inventors Wasson et al., filed May 30, 2018 and issued May 12, 2020, discloses a system includes aAttorney Docket No.4604-002PCT controller configured to determine a set of background light intensities associated with a satellite, where each background light intensity corresponds to at least one of an orientation and a position of a light source relative to the satellite, to determine a set of relative orientations of the light source corresponding to the set of background light intensities, and to generate an image of the satellite based, at least in part, on the determined set of background light intensities and the determined set of relative orientations of the light source.

[0012] US Patent No.11,496,679 for Real-time satellite imaging system by inventor Williams filed February 8, 2021 and issued November 8, 2022, discloses methods and apparatus for Real-time Satellite Imaging System. More particularly, one embodiment of the present invention an imaging sensor on a geostationary satellite having one or more co-collimated telescopes. The telescopes illuminate local planes which are sparsely populated with focal plane arrays. The focal plane arrays record the entire observable Earth hemisphere at one time, at least once every ten seconds.

[0013] US Patent No.7,090,170 for In-orbit satellite sensor alignment determination by inventor Kau, filed November 22, 2002 and issued August 15, 2006, discloses a sensor alignment system and method is provided that facilitates the precise alignment determination of satellite sensors. The system and method utilizes an Inertial Measurement Unit (IMU) to facilitate alignment determination of multiples sensors on a satellite. The system and method performs a roll of the satellite around a preliminary sensor active axis, using the IMU to measure the rotation rate in both magnitude and direction. The sensor input is monitored by the IMU during the roll around the preliminary sensor axis. The data from sensor output obtained during the roll can be processed to calculate the difference between the preliminary sensor axis and the actual sensor axis. From this calculation the actual alignment of the sensor axis can be determined. Furthermore, by performing this alignment determination operation for multiple sensors the relative alignment between sensors can be determined.

[0014] US Patent Publication No.2020 / 0371373 for Focal plane assembly of remote sensing satellite and image processing method thereof by inventors Ling et al., filed June 24, 2019 and published November 26, 2020, discloses a Focal Plane Assembly (FPA) of a remote sensing satellite for receiving a focal plane image provided by an optical lens, comprises a sub-pixel shifting field separator, a first linear image sensor, and a second linear image sensor. The field separator split the focal plane image up into a first half focal plane image and a second half focal plane image, the first linear image sensor, located at an edge of a half focal plane, receives the first half focal plane image to generate a first image, the second linear image sensor, located at an edge of another half focal plane, receives the second half focal plane image to generate a second image, wherein a sub-pixel shifting relation is between the first image and the second image.Attorney Docket No.4604-002PCT

[0015] US Patent Publication No.2022 / 0242593 for Artificial satellite and control method thereof by inventors Ezawa, et al., filed December 3, 2021 and published August 4, 2022, discloses an artificial satellite and a control method thereof that enable to ensure quality of a captured image while suppressing battery consumption. An artificial satellite includes: an imaging device configured to perform imaging of a predetermined region on the ground; and a management unit configured to change accuracy of attitude control in accordance with a remaining battery amount at an instructed imaging time, and configured to change an imaging condition in accordance with accuracy of the attitude control. The present technology can be applied to, for example, an artificial satellite or the like that performs satellite remote sensing by formation flight.

[0016] Chinese Patent No.110,516,588 for Remote sensing satellite system by inventors Weijian et al., filed August 23, 2019 and issued April 18, 2023, discloses a remote sensing satellite system which comprises a first satellite, wherein the first satellite comprises at least four image sensors, the at least four image sensors are used for simultaneously acquiring images of the ground, the ground areas acquired by the at least four image sensors are completely or partially overlapped, the spatial resolution and the spectral resolution of the images acquired by the at least four image sensors are different from each other, and the first satellite is used for carrying out image fusion on at least one part of the images acquired by the at least four image sensors so as to generate a fused remote sensing image. The invention can efficiently obtain the remote sensing image with high definition by using the limited resources of the satellite.

[0017] Chinese Patent No.109,018,432 for High-precision comprehensive remote sensing satellite layout for multi-load cooperative observation by inventors Jinru et al., filed June 19, 2018 and issued May 29, 2020, discloses a high-precision comprehensive remote sensing satellite layout for multi-load cooperative observation, which effectively ensures harsh working environments of active detection loads such as laser radars and the like through an eccentric deflection high-precision high-stability installation layout; by means of common reference installation, transmission path reduction and the like, the requirement of low-deformation precision cooperative observation of dual-polarization load angle grading view field registration is met, and an interface between systems is simplified; based on the existing mixed nested layered stepped satellite platform configuration, the overall installation layout of the complex constraint load / antenna / attitude sensor with the same platform, various types, different envelopes, weights and use requirements, and multi-hand synthesis is realized, the satellite development risk and cost are reduced, and the satellite development period is shortened. The invention can be applied to the low-orbit comprehensive remote sensing satellite with the cooperative observation requirements of the loads with different envelopes and different weightsAttorney Docket No.4604-002PCT on the same platform, which has the advantages of large volume envelope, large concentration mass, large heat flow density, high-precision and high-stability installation and complex visual field constraint.

[0018] Chinese Patent Publication No.109,844,471 for Spectral luminosity measuring device with multiple spectral measurement wave bands by inventor Pasternak, filed September 29, 2017 and published April 27, 2021, discloses a spectrophotometric measuring device has a plurality of spectral measuring bands, including a single telescope and a single spectrophotometer. A plurality of spectral bands are obtained by placing aperture splitting prisms at the entrance aperture (PE) of the telescope and by using a spectral band selection filter. Such devices are lightweight, small in size and low in cost. In particular, it can be integrated into satellites, in particular for the task of characterizing the flow of carbon compounds generated at the surface of the earth.

[0019] Chinese Patent Publication No.108,557,114 for A kind of distribution remote sensing satellite by inventors Yong et al., filed April 18, 2018 and published September 21, 2018, discloses a kind of distributed remote sensing satellites comprising a service star and six remote sensing unit stars, and distributed formation mode or synthetic aperture integrated mode can be used in the service star and remote sensing unit star.

[0020] Canadian Patent No.3067604 for System and method for widespread low cost orbital satellite access by inventor Platzer, filed February 3, 2014 and issued July 12, 2022, discloses a large constellation of low-cost satellites with a satellite support and administration system that allows widespread user access to advanced satellite technology at extremely low costs. Any portion of the constellation can be tasked and configured for specific data capture. In one embodiment, a constellation of individual satellites are employed to concurrently collect occultation data from multiple GPSS originating signals that pass through atmospheric sections of interest. Alternately, the constellation can be configured as a vehicle location tracking system that receives multiple vehicle tracking signals and based thereon, track within a system grid each vehicle under surveillance. The system can use AIS for ocean going vessels, ADS-B for aircraft, and AEI for trains. Use of the system permits extended tracking of key cargos and the protection of vehicles from piracy and the like. SUMMARY OF THE INVENTION

[0021] The present invention is generally directed to an artificial satellite having more than one sensor, and more specifically to individual artificial satellites including optical sensors, hyperspectral sensors, video generators, and ultraviolet sensors.Attorney Docket No.4604-002PCT

[0022] It is an object of this invention to provide a single artificial satellite with a plurality of sensor types, providing for greater data collection than traditional satellites that operate with only a single sensor.

[0023] In one embodiment, the present invention is related to an artificial satellite, including at least one computer processor including a memory, a plurality of sensors mounted to at least one gimbal, and a transceiver, wherein the plurality of sensors are operable to capture image data, wherein the at least one computer processor is operable to automatically correct the image data, wherein the at least one computer processor is operable to fuse the image data, and wherein the transceiver is operable to transmit the fused image data.

[0024] In another embodiment, the present invention is related to an artificial satellite, including at least one computer processor including a memory, a plurality of sensors, at least one solar cell operable to power the plurality of sensors and the at least one computer processor, and a transceiver, wherein the plurality of sensors are operable to capture image data, wherein the at least one computer processor is operable to automatically correct the image data, wherein the at least one computer processor is operable to fuse the image data, and wherein the transceiver is operable to transmit the fused image data.

[0025] In yet another embodiment, the present invention is related to an artificial satellite, including at least one computer processor including a memory, a plurality of sensors each mounted to separate gimbals, and a transceiver, wherein each of the plurality of sensors are operable to orient towards a common target, wherein each of the plurality of sensors are operable to capture image data from the common target, wherein the at least one computer processor is operable to automatically correct the image data via orthorectification, radiometric correction, and / or pan sharpening, wherein the at least one computer processor is operable to fuse the image data, and wherein the transceiver is operable to transmit the fused image data.

[0026] These and other aspects of the present invention will become apparent to those skilled in the art after a reading of the following description of the preferred embodiment when considered with the drawings, as they support the claimed invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0027] FIG.1 illustrates a perspective view of an artificial satellite with a plurality of sensors according to one embodiment of the present invention.

[0028] FIG.2 illustrates a perspective view of a sensor array of a satellite according to one embodiment of the present invention.

[0029] FIG.3 is a schematic diagram of a system of the present invention. DETAILED DESCRIPTIONAttorney Docket No.4604-002PCT

[0030] The present invention is generally directed to an artificial satellite having more than one sensor, and more specifically to individual artificial satellites including optical sensors, hyperspectral sensors, video generators, and ultraviolet sensors.

[0031] In one embodiment, the present invention is related to an artificial satellite, including at least one computer processor including a memory, a plurality of sensors mounted to at least one gimbal, and a transceiver, wherein the plurality of sensors are operable to capture image data, wherein the at least one computer processor is operable to automatically correct the image data, wherein the at least one computer processor is operable to fuse the image data, and wherein the transceiver is operable to transmit the fused image data.

[0032] In another embodiment, the present invention is related to an artificial satellite, including at least one computer processor including a memory, a plurality of sensors, at least one solar cell operable to power the plurality of sensors and the at least one computer processor, and a transceiver, wherein the plurality of sensors are operable to capture image data, wherein the at least one computer processor is operable to automatically correct the image data, wherein the at least one computer processor is operable to fuse the image data, and wherein the transceiver is operable to transmit the fused image data.

[0033] In yet another embodiment, the present invention is related to an artificial satellite, including at least one computer processor including a memory, a plurality of sensors each mounted to separate gimbals, and a transceiver, wherein each of the plurality of sensors are operable to orient towards a common target, wherein each of the plurality of sensors are operable to capture image data from the common target, wherein the at least one computer processor is operable to automatically correct the image data via orthorectification, radiometric correction, and / or pan sharpening, wherein the at least one computer processor is operable to fuse the image data, and wherein the transceiver is operable to transmit the fused image data.

[0034] These and other aspects of the present invention will become apparent to those skilled in the art after a reading of the following description of the preferred embodiment when considered with the drawings, as they support the claimed invention.

[0035] None of the prior art discloses a single artificial satellite operable to support a plurality of sensors as disclosed in the present application, especially a plurality of sensors for imaging, optically or otherwise, terrestrial features. More particularly, none of the prior art includes a single satellite carrying two hyperspectral imagers, two ultraviolet (UV) telescopes, a visible video imager, an IR spectrometer, an AIS receiver, and a Forward Looking Imager (FLI).

[0036] Artificial satellites have a variety of uses and have become an integral part of modern life. Artificial satellites aid in Earth observation, outer space observation, communication systems, navigation systems, and even weapon systems. Including a plurality of sensor types inAttorney Docket No.4604-002PCT Earth observation is important as there are some features that are best seen or even only able to be seen utilizing specific types of sensors. Typical satellite systems include a plurality of satellites, each carrying a single sensor that intercommunicate and send their data down to a ground link, where sensor fusion is able to be carried out on the sensor data from multiple satellites. Utilizing a single satellite with multiple sensors provides several benefits, especially for systems where processing is performed onboard the satellite, as the system is less reliant on ensuring clear lines of communication with all satellites in a constellation in order to obtain all the necessary sensor data. Furthermore, integrating a plurality of sensors on a single satellite reduces the complications of later sensor fusion as the sensors are gathering data on the same areas from approximately the same place and from approximately the same angle. However, artificial satellites include electricity generation systems, such as solar panels, to power the onboard equipment. Importantly, artificial satellites require a power generation system operable to produce enough power to support its onboard equipment, otherwise the equipment cannot function. Consequently, the greater the number of sensors or the greater the power demand of the sensors, the more power need by the power generation system. Therefore, there is a need for an artificial satellite capable of supporting multiple sensors.

[0037] In one embodiment, the artificial satellite includes at least two sensors. In one embodiment, the artificial satellite includes at least three sensors. In one embodiment, the artificial satellite includes at least four sensors. In one embodiment, the artificial satellite includes at least five sensors. In one embodiment, the artificial satellite includes at least three sensors wherein at least one sensor is a high-power, high-resolution sensor. In one embodiment, the artificial satellite includes a plurality of sensors.

[0038] In one embodiment, the artificial satellite is of a small size and is not a large spacecraft. In one embodiment, the artificial satellite weighs approximately 180 kg.

[0039] One of ordinary skill in the art will understand that the inclusion of onboard processing and multiple sensors on a single satellite does not mean that the satellite of the present invention is not able to be included in a constellation of a plurality of satellites. In one embodiment, a satellite of the present invention is included in a constellation of 15 satellites, or any other number of satellites. In some embodiments, use of a plurality of satellites according to the present invention provides an advantage due to the different angles at which different satellites in the constellation are able to observe the same feature or different features, even if the different satellites include substantially the same type of sensors.

[0040] In one embodiment, the satellite is able to communicate with ground stations or with other satellites in a constellation via S-band (approximately 2-4 GHz, or more particularly 2.31- 2.36 GHz, 2-2.2 GHz, or approximately 2.6 GHz), X-band (approximately 7-11.2 GHz, or moreAttorney Docket No.4604-002PCT particularly 7.25 GHz to 7.75 GHz or 7.9 GHz to 8.4 GHz), low latency L-band (approximately 1-2 GHz, or more particularly frequencies such as 1176.45 MHz, 1227.6 MHz, 1381.05 MHz, or 1575.42 MHz), via optical inter-satellite link (OISL) communications, or via Ka-band radar (between approximately 26.5-40 GHz, or more particularly between approximately 27 GHz and 31 GHz).

[0041] In a preferred embodiment, the plurality of sensors includes a Red, Blue, and Green (RGB), an optical sensor, two hyperspectral sensors, one automatic identification system (AIS) receiver, and two ultraviolet instruments (e.g., two ultraviolet telescopes). In one embodiment, the plurality of sensors includes any number or combination of at least one RGB video telescope, at least one hyperspectral sensor, at least one ultraviolet instrument, at least one infrared spectrometer, and / or at least one AIS receiver. In one embodiment, the plurality of sensors include one or more optical sensors, one or more hyperspectral sensors, one or more infrared sensors (e.g., infrared cameras, infrared telescopes, infrared spectrometers, etc.), one or more ultraviolet sensors, one or more AIS receivers, one or more radiofrequency receivers, one or more dosimeters, one or more magnetometers, one or more LiDAR sensors, one or more spectrometers, one or more automatic dependent surveillance-broadcast (ADS-B) systems, and / or one or more synthetic aperture radar (SAR) systems. In one embodiment, the artificial satellite includes at least one RGB video telescope and at least one hyperspectral sensor. In one embodiment, the artificial satellite includes at least one RGB video telescope, at least one hyperspectral sensor, and at least one ultraviolet instrument. In one embodiment, the artificial satellite includes at least one RGB video telescope, at least one hyperspectral sensor, at least one ultraviolet instrument, and at least one infrared telescope. In one embodiment, the plurality of sensors includes any combination of five or fewer of the aforementioned sensors.

[0042] In one embodiment, the plurality of sensors are operable to capture image data. In one embodiment, the artificial satellite includes at least one transmitter operable to transmit the image data from the plurality of sensors. In one embodiment, the artificial satellite includes at least one transceiver operable to transmit and receive data.

[0043] In one embodiment, the satellite includes a plurality of onboard processing computers configured to perform tasks such as sensor fusion and other processing of the data generated from the plurality of sensors. In a preferred embodiment, the satellite includes two flight processors (i.e., processors dedicated to tasks relating to the movement and navigation of the satellite) and four payload processors (i.e., processors dedicated to processing tasks related to the sensors), but one of ordinary skill in the art will understand that other combinations of flight and payload computers are also contemplated herein. In one embodiment, the satellite includes approximately 10 TB of memory storage.Attorney Docket No.4604-002PCT

[0044] Examples of processing tasks able to be performed by the payload processors onboard the satellite include orthorectification, other georectification, radiometric correction, and pan sharpening, among others. Orthorectification is a form of georectification that is important for removing distortion from the image data produced by sensors onboard the satellite, and is especially important such that measurements such as distances, angles, and areas of features in the image data is able to be accurately determined. The distortion corrected in orthorectification is typically caused by differences in elevation of the area being imaged (e.g., due to mountains, valleys, buildings, etc.), the curvature of the Earth, the tilt of the imaging device on the satellite, and the movement of the satellite while the image is being generated. Without orthorectification, the elevation differences cause the actual position of imaged objects to be displaced from their actual position, making tasks that require actual mapping difficult if not impossible. In the prior art, this process of orthorectification occurs on a ground station after image data from the satellite is received, using a digital elevation model (DEM), commonly generated from multiple full passes of satellite mapping by separate satellites, which often include LiDAR, Radar, or stereophotogrammetric based sensors. However, this process introduces large amounts of latency, both in the generation of a sufficient DEM model to provide an accurate orthorectification, and in the actual transmission back to a ground station for the post-processing.

[0045] In one embodiment, the plurality of sensors are mounted on at least one gimbal. In one embodiment, the at least one gimbal is a pivoted support member that permits rotation about a plurality of axes. In one embodiment, the gimbal enables the plurality of sensors to rotate independent of the movement or rotation of the artificial satellite. In one nonlimiting example, the at least one gimbal enables the plurality of sensors to be directed towards the Earth while the artificial satellite, or the solar array of the artificial satellite in one embodiment, is directed towards the sun.

[0046] In one embodiment, the at least one RGB video telescope is operable to capture 8K full-color video.

[0047] In one embodiment, the at least one hyperspectral sensor is operable to produce 5- meter resolution hyperspectral imaging. The hyperspectral imaging includes chemistry data for agriculture, security, energy, and environmental monitoring. The hyperspectral sensor is operable to capture 440 bands of electromagnetic data. The hyperspectral sensor is operable to collect electromagnetic data in a series of set images with each image representing a specific narrow wavelength. The images are then combined to create a three-dimensional hyperspectral data set for processing and analysis. In one embodiment, the hyperspectral data set includes x and y coordinates representing two spatial dimensions of the captured area with a third λ coordinate representing the spectral dimension or range of wavelengths captured.Attorney Docket No.4604-002PCT

[0048] In one embodiment, the at least one ultraviolet instrument is operable to capture electromagnetic radiation data in the ultraviolet range (100 – 400 nm). In this embodiment, the ultraviolet telescope is operable to capture line spectrum data within the ultraviolet range to determine chemical compositions, densities, and temperatures of the captured area. Advantageously, the ultraviolet instrument provides information about the evolution of galaxies, the presence of hot white dwarfs, and main sequences in orbit around cooler stars.

[0049] In one embodiment, the at least one infrared spectrometer is operable to capture electromagnetic radiation data in the infrared range (780 – 1000 nm). In this embodiment, the infrared spectrometer is operable to capture line spectrum data within the infrared range to monitor greenhouse gases in the captured area. In one embodiment, the infrared spectrometer is operable to produce infrared spectrum data. Infrared spectrum data is visualized on a graph with a vertical axis of infrared light absorbance against frequency, wavenumber, and / or wavelength on the horizontal axis.

[0050] In one embodiment, the at least one AIS receiver is operable to receive AIS signatures from ships for vessel traffic services (VTS). In one embodiment, the AIS signatures include unique identification, position, course, and speed data. In one embodiment, the artificial satellite is operable to deconflict AIS signatures. In one embodiment, the artificial satellite includes a transceiver operable to transmit the AIS signatures. Advantageously, by inclusion of the AIS receiver, the artificial satellite assists vessels’ watchstanding officers and enables maritime authorities to track and monitor vessel movement.

[0051] In one embodiment, the plurality of sensors are operable to capture image data from the Earth for Earth observation, weather forecasting, agriculture monitoring, and / or greenhouse gas monitoring. In one embodiment, the plurality of sensors are operable to capture image data from outer space to collect information about planets, meteorites, stars, distant galaxies, and / or other outer space objects.

[0052] In one embodiment, the plurality of sensors are all directed to a common target, simultaneously and are operable to obtain image data from the plurality of sensors on the same common target. In this embodiment, the image data is combined, overlayed, and / or integrated for analytical purposes.

[0053] In one embodiment, the artificial satellite includes a power system operable to produce enough power to support the plurality of sensors and / or analysis of image data captured by the plurality of sensors.

[0054] In order to provide sufficient power in order to support the multiple sensors onboard the satellite and the electric propulsion system of the satellite, in one embodiment, the satellite includes power systems providing approximately 1 kW of power. In one embodiment, the powerAttorney Docket No.4604-002PCT is provided by one or more solar cells of the satellite, one or more batteries, and / or combinations thereof.

[0055] Referring now to the drawings in general, the illustrations are for the purpose of describing one or more preferred embodiments of the invention and are not intended to limit the invention thereto.

[0056] FIG.1 illustrates a perspective view of an artificial satellite 100 with a plurality of sensors 102 according to one embodiment of the present invention. In one embodiment, the plurality of sensors 102 are mounted to a top center side of the artificial satellite 100. In one embodiment, the artificial satellite 100 includes a plurality of solar panels 104. In one embodiment, the plurality of solar panels 104 and / or one or more onboard battery systems of the artificial satellite 100 are used to provide sufficient power for the multiple sensors and / or processors for processing and / or combining the sensor data onboard the individual satellites, allowing for larger, more complicated, and higher energy-use payloads than have existed in previous satellite systems. One of ordinary skill in the art will understand that the types of battery systems able to be used on the satellite include, but are not limited to, carbon-zinc, lead-acid, nickel-cadmium, nickel-hydrogen, silver zinc, and / or lithium-ion battery systems and are able to include a variety of different numbers and sizes of batteries in order to meet the energy demand requirements of the payload onboard.

[0057] In one embodiment, the artificial satellite of the present invention includes the features (e.g., the hinge-lock mechanism for the expanding solar array) described in U.S. Provisional Patent Application No.63 / 589,135, filed October 10, 2023, which is incorporated herein by reference in its entirety.

[0058] FIG.2 illustrates a perspective view of a sensor array of a satellite according to one embodiment of the present invention. The satellite 200 includes a plurality of sensors extending outwardly from a single surface 202 of the satellite 200. In one embodiment, the plurality of sensors includes a first hyperspectral sensor 204 and a second hyperspectral sensor 208. The first hyperspectral sensor 204 is mounted on a first gimbal 206 configured to rotate the first hyperspectral sensor 204 along a plurality of rotational axes. In one embodiment, the first gimbal 206 is itself positioned atop one or more base platforms extending upwardly from the surface 202, where the one or more base platforms are configured to rotate to provide an additional degree of freedom for the system. The second hyperspectral sensor 208 is mounted on a second gimbal 210 configured to rotate the second hyperspectral sensor 210 along a plurality of rotational axes. In one embodiment, the second gimbal 210 is itself positioned atop one or more base platforms extending upwardly from the surface 202, where the one or more base platforms are configured to rotate to provide an additional degree of freedom for the system. In oneAttorney Docket No.4604-002PCT embodiment, the first gimbal 206 and the second gimbal 210 are attached to different base platforms and therefore are rotationally decoupled, while in another embodiment, both the first gimbal 206 and the second gimbal 210 are connected to the same one or more base platforms.

[0059] Hyperspectral sensors offer a wide variety of benefits, including providing for high resolution enhancing of image data generated by the other sensors. In one embodiment, the first hyperspectral sensor 204 has a field of view along a first axis of 2.2 degrees and a field of view along a second axis (orthogonal to the first axis) of 1.7 degrees. In one embodiment, the second hyperspectral sensor 208 has a field of view along a first axis of 2.2 degrees and a field of view along a second axis (orthogonal to the first axis) of 1.7 degrees. In one embodiment, the first hyperspectral sensor 204 has a swath width of approximately 20.4 km and a swath height of approximately 20.4 km. In one embodiment, the second hyperspectral sensor 208 has a swath width of approximately 20.4 km and a swath height of approximately 20.4 km. In one embodiment, the first hyperspectral sensor 204 has a ground sample distance (GSD) of approximately 5 m. In one embodiment, the second hyperspectral sensor 208 has a ground sample distance (GSD) of approximately 5 m. In one embodiment, the first hyperspectral sensor 204 operates in 32 spectral bands between approximately 440 nm and approximately 880 nm. In one embodiment, the second hyperspectral sensor 208 operates in 32 spectral bands between approximately 440 nm and approximately 880 nm. In one embodiment, the first hyperspectral sensor 204 is operable to generate an image with up to approximately 16.8 million pixels. In one embodiment, the second hyperspectral sensor 208 is operable to generate an image with up to approximately 16.8 million pixels. In one embodiment, the file sizes produced by the first hyperspectral sensor 204 are equal to approximately 768 MB. In one embodiment, the file sizes produced by the second hyperspectral sensor 208 are equal to approximately 768 MB.

[0060] Visual video imaging systems provide for full video satellite imaging, preferably 8K full-color video according to the present invention, which is able to be enhanced via sensor fusion with data produced by one or more of the other sensor types. In one embodiment, the satellite 200 includes at least one visual video imaging system 212 (e.g., an electro-optical red- green-blue (EO RGB) sensor). In one embodiment, the at least one visual video imaging system 212 extends from approximately the center of the surface 202 of the satellite 200. In one embodiment, the at least one visual video imaging system 212 has a field of view along a first axis of 1.6 degrees and a field of view along a second axis (orthogonal to the first axis) of 1.2 degrees. In one embodiment, the at least one visual video imaging system 212 has a swath width of approximately 14.7 km and a swath height of approximately 11 km. In one embodiment, the at least one visual video imaging system 212 has a ground sample distance (GSD) of approximately 1.6 m. In one embodiment, the at least one visual video imaging system 212 operates in 3Attorney Docket No.4604-002PCT spectral bands between approximately 450 nm and approximately 670 nm. In one embodiment, the at least one visual video imaging system 212 is operable to generate an image with up to approximately 65.4 million pixels. In one embodiment, the file sizes produced by the at least one visual video imaging system 212 are equal to approximately 78 MB.

[0061] The inclusion of ultraviolet sensors provides for particular utility for the space domain awareness of the satellite as well as for use in astronomical purposes to identify remote sources producing in the UV range. In one embodiment, a first ultraviolet (UV) sensor 214 (e.g., a first UV telescope) and a second UV sensor 216 (e.g., a second UV telescope) extends outwardly from the surface 202 of the satellite 200. In one embodiment, the first UV sensor 214 is positioned directly adjacent to the second UV sensor 216, but one of ordinary skill in the art will understand that other relevant positionings of the first UV sensor 214 and the second UV sensor 216 are contemplated herein. In one embodiment, the first UV sensor 214 has a field of view along a first axis of 1.1 degrees and a field of view along a second axis (orthogonal to the first axis) of 1.1 degrees. In one embodiment, the second UV sensor 216 has a field of view along a first axis of 1.1 degrees and a field of view along a second axis (orthogonal to the first axis) of 1.1 degrees. In one embodiment, the first UV sensor 214 has a swath width of approximately 10.5 km and a swath height of approximately 10.5 km. In one embodiment, the second UV sensor 216 has a swath width of approximately 10.5 km and a swath height of approximately 10.5 km. In one embodiment, the first UV sensor 214 has a ground sample distance (GSD) of approximately 5.1 m. In one embodiment, the second UV sensor 216 has a ground sample distance (GSD) of approximately 5.1 m. In one embodiment, the first UV sensor 214 operates at wavelengths between approximately 220 nm and approximately 240 nm. In one embodiment, the second UV sensor 216 operates at wavelengths between approximately 250 nm and approximately 350 nm. In one embodiment, the first UV sensor 214 is operable to generate an image with up to approximately 4.2 million pixels. In one embodiment, the second UV sensor 216 is operable to generate an image with up to approximately 4.2 million pixels. In one embodiment, the file sizes produced by the first UV sensor 214 are equal to approximately 6 MB. In one embodiment, the file sizes produced by the second UV sensor 216 are equal to approximately 6 MB.

[0062] In one embodiment, a platform 218 extends outwardly from the surface 202 of the satellite 200. In one embodiment, a forward looking imager (FLI) 220 is attached to a top surface of the platform 218. In one embodiment, an infrared (IR) spectrometer 222 also is attached to top surface of the platform 218. In one embodiment, the platform 218 includes one or more lower shelves and an AIS receiver 224 is positioned on and attached to one of the lower shelves of the platform 218. One of ordinary skill in the art will understand that configurations wherein the IRAttorney Docket No.4604-002PCT spectrometer 222, the FLI 220 and the AIS receiver 224 are attached to different platforms or structures extending from the surface 202 are also contemplated herein.

[0063] Inclusion of infrared sensors allows for the present invention to generate heat maps of large areas for monitoring of large scale climate phenomena, including greenhouse gas emission detection according to one embodiment. In one embodiment, the IR spectrometer 222 has a field of view along a first axis of 0.15 degrees and a field of view along a second axis (orthogonal to the first axis) of 0.15 degrees. In one embodiment, the IR spectrometer 222 has a swath width of approximately 1.4 km and a swath height of approximately 1.4 km. In one embodiment, the IR spectrometer 222 has a ground sample distance (GSD) of approximately 1376 m. In one embodiment, the IR spectrometer 222 operates in approximately 100 spectral bands in a short- wave infrared range (SWIR) between approximately 1,350 nm and approximately 2,100 nm.

[0064] While the hyperspectral imagers provide for higher resolution images across a small area, the inclusion of a wide field of view (FOV) visual sensor, providing for greater utility in particular use cases, such as weather evaluation, cloud detection, ship tracking, space domain awareness, and / or other tasks that benefit from wider fields of vision. In one embodiment, the FLI 220 has a field of view along a first axis of 63 degrees and a field of view along a second axis (orthogonal to the first axis) of 47 degrees. In one embodiment, the FLI 220 has a swath width of approximately 1051 km and a swath height of approximately 575 km. In one embodiment, the FLI 220 has a ground sample distance (GSD) of approximately 250 m. In one embodiment, the FLI 220 operates in 3 spectral bands between approximately 400 nm and approximately 900 nm. In one embodiment, the FLI 220 is operable to generate an image with up to approximately 3.1 million pixels. In one embodiment, the file sizes produced by the FLI 220 are equal to approximately 4.5 MB.

[0065] Inclusion of an AIS Receiver allows for ship tracking capabilities for improved maritime domain awareness, which provides benefits for defense, shipping protection, or insurance purposes, among others. In one embodiment, the AIS Receiver 224 has a field of view along a first axis of 84 degrees and a field of view along a second axis (orthogonal to the first axis) of 84 degrees. In one embodiment, the AIS Receiver 224 has a swath width of approximately 5000 km and a swath height of approximately 5000 km.

[0066] One of ordinary skill in the art will understand that the specific positioning of each sensor along the surface 202 is not intended to be limited according to the present invention, and the satellite 200 is therefore able to tolerate a plurality of different orientations necessary to accommodate the sensor devices being used and associated supports for each sensor device.

[0067] Additionally, one of ordinary skill in the art will understand that the present invention further contemplates types of sensors beyond those shown in and discussed with regard to FIG.2,Attorney Docket No.4604-002PCT including but not limited to one or more dazzle sensors (serving to detect hostile lasing and dazzling for disrupting operations of the satellite), one or more small scale synthetic aperture (SAR) radar systems, one or more LiDAR sensors, one or more thermal infrared sensors (e.g., for pattern of life mapping, for space domain awareness, for terrestrial search / tip-and-cue operations, etc.), one or more long-wave infrared sensors, one or more wide area UV sensors (e.g., for space weather or terrestrial communication alerts), one or more radiofrequency (RF) signal detectors (e.g., for pattern of life, tip-and-cue operations, etc.), and / or one or more other types of sensors or signal receivers.

[0068] FIG.3 is a schematic diagram of an embodiment of the invention illustrating a computer system, generally described as 800, having a network 810, a plurality of computing devices 820, 830, 840, a server 850, and a database 870.

[0069] The server 850 is constructed, configured, and coupled to enable communication over a network 810 with a plurality of computing devices 820, 830, 840. The server 850 includes a processing unit 851 with an operating system 852. The operating system 852 enables the server 850 to communicate through network 810 with the remote, distributed user devices. Database 870 is operable to house an operating system 872, memory 874, and programs 876.

[0070] In one embodiment of the invention, the system 800 includes a network 810 for distributed communication via a wireless communication antenna 812 and processing by at least one mobile communication computing device 830. Alternatively, wireless and wired communication and connectivity between devices and components described herein include wireless network communication such as WI-FI, WORLDWIDE INTEROPERABILITY FOR MICROWAVE ACCESS (WIMAX), Radio Frequency (RF) communication including RF identification (RFID), NEAR FIELD COMMUNICATION (NFC), BLUETOOTH including BLUETOOTH LOW ENERGY (BLE), ZIGBEE, Infrared (IR) communication, cellular communication, satellite communication, Universal Serial Bus (USB), Ethernet communications, communication via fiber-optic cables, coaxial cables, twisted pair cables, and / or any other type of wireless or wired communication. In another embodiment of the invention, the system 800 is a virtualized computing system capable of executing any or all aspects of software and / or application components presented herein on the computing devices 820, 830, 840. In certain aspects, the computer system 800 is operable to be implemented using hardware or a combination of software and hardware, either in a dedicated computing device, or integrated into another entity, or distributed across multiple entities or computing devices.

[0071] By way of example, and not limitation, the computing devices 820, 830, 840 are intended to represent various forms of electronic devices including at least a processor and a memory, such as a server, blade server, mainframe, mobile phone, personal digital assistantAttorney Docket No.4604-002PCT (PDA), smartphone, desktop computer, netbook computer, tablet computer, workstation, laptop, and other similar computing devices. The components shown here, their connections and relationships, and their functions, are meant to be exemplary only, and are not meant to limit implementations of the invention described and / or claimed in the present application.

[0072] In one embodiment, the computing device 820 includes components such as a processor 860, a system memory 862 having a random access memory (RAM) 864 and a read- only memory (ROM) 866, and a system bus 868 that couples the memory 862 to the processor 860. In another embodiment, the computing device 830 is operable to additionally include components such as a storage device 890 for storing the operating system 892 and one or more application programs 894, a network interface unit 896, and / or an input / output controller 898. Each of the components is operable to be coupled to each other through at least one bus 868. The input / output controller 898 is operable to receive and process input from, or provide output to, a number of other devices 899, including, but not limited to, alphanumeric input devices, mice, electronic styluses, display units, touch screens, gaming controllers, joy sticks, touch pads, signal generation devices (e.g., speakers), augmented reality / virtual reality (AR / VR) devices (e.g., AR / VR headsets), or printers.

[0073] By way of example, and not limitation, the processor 860 is operable to be a general- purpose microprocessor (e.g., a central processing unit (CPU)), a graphics processing unit (GPU), a microcontroller, a Digital Signal Processor (DSP), an Application Specific Integrated Circuit (ASIC), a Field Programmable Gate Array (FPGA), a Programmable Logic Device (PLD), a controller, a state machine, gated or transistor logic, discrete hardware components, or any other suitable entity or combinations thereof that can perform calculations, process instructions for execution, and / or other manipulations of information.

[0074] In another implementation, shown as 840 in FIG.3, multiple processors 860 and / or multiple buses 868 are operable to be used, as appropriate, along with multiple memories 862 of multiple types (e.g., a combination of a DSP and a microprocessor, a plurality of microprocessors, one or more microprocessors in conjunction with a DSP core).

[0075] Also, multiple computing devices are operable to be connected, with each device providing portions of the necessary operations (e.g., a server bank, a group of blade servers, or a multi-processor system). Alternatively, some steps or methods are operable to be performed by circuitry that is specific to a given function.

[0076] According to various embodiments, the computer system 800 is operable to operate in a networked environment using logical connections to local and / or remote computing devices 820, 830, 840 through a network 810. A computing device 830 is operable to connect to a network 810 through a network interface unit 896 connected to a bus 868. Computing devices areAttorney Docket No.4604-002PCT operable to communicate communication media through wired networks, direct-wired connections or wirelessly, such as acoustic, RF, or infrared, through an antenna 897 in communication with the network antenna 812 and the network interface unit 896, which are operable to include digital signal processing circuitry when necessary. The network interface unit 896 is operable to provide for communications under various modes or protocols.

[0077] In one or more exemplary aspects, the instructions are operable to be implemented in hardware, software, firmware, or any combinations thereof. A computer readable medium is operable to provide volatile or non-volatile storage for one or more sets of instructions, such as operating systems, data structures, program modules, applications, or other data embodying any one or more of the methodologies or functions described herein. The computer readable medium is operable to include the memory 862, the processor 860, and / or the storage media 890 and is operable be a single medium or multiple media (e.g., a centralized or distributed computer system) that store the one or more sets of instructions 900. Non-transitory computer readable media includes all computer readable media, with the sole exception being a transitory, propagating signal per se. The instructions 900 are further operable to be transmitted or received over the network 810 via the network interface unit 896 as communication media, which is operable to include a modulated data signal such as a carrier wave or other transport mechanism and includes any delivery media. The term “modulated data signal” means a signal that has one or more of its characteristics changed or set in a manner as to encode information in the signal.

[0078] Storage devices 890 and memory 862 include, but are not limited to, volatile and non- volatile media such as cache, RAM, ROM, EPROM, EEPROM, FLASH memory, or other solid state memory technology; discs (e.g., digital versatile discs (DVD), HD-DVD, BLU-RAY, compact disc (CD), or CD-ROM) or other optical storage; magnetic cassettes, magnetic tape, magnetic disk storage, floppy disks, or other magnetic storage devices; or any other medium that can be used to store the computer readable instructions and which can be accessed by the computer system 800.

[0079] In one embodiment, the computer system 800 is within a cloud-based network. In one embodiment, the server 850 is a designated physical server for distributed computing devices 820, 830, and 840. In one embodiment, the server 850 is a cloud-based server platform. In one embodiment, the cloud-based server platform hosts serverless functions for distributed computing devices 820, 830, and 840.

[0080] It is also contemplated that the computer system 800 is operable to not include all of the components shown in FIG.3, is operable to include other components that are not explicitly shown in FIG.3, or is operable to utilize an architecture completely different than that shown in FIG.3. The various illustrative logical blocks, modules, elements, circuits, and algorithmsAttorney Docket No.4604-002PCT described in connection with the embodiments disclosed herein are operable to be implemented as electronic hardware, computer software, or combinations of both. To clearly illustrate this interchangeability of hardware and software, various illustrative components, blocks, modules, circuits, and steps have been described above generally in terms of their functionality. Whether such functionality is implemented as hardware or software depends upon the particular application and design constraints imposed on the overall system. Skilled artisans may implement the described functionality in varying ways for each particular application (e.g., arranged in a different order or partitioned in a different way), but such implementation decisions should not be interpreted as causing a departure from the scope of the present invention.

[0081] Certain modifications and improvements will occur to those skilled in the art upon a reading of the foregoing description. The above-mentioned examples are provided to serve the purpose of clarifying the aspects of the invention and it will be apparent to one skilled in the art that they do not serve to limit the scope of the invention. All modifications and improvements have been deleted herein for the sake of conciseness and readability but are properly within the scope of the present invention.

Claims

AMENDED CLAIMS received by the International Bureau on 12 August 2025 (12.08.2025)

1. An artificial satellite, comprising: at least one computer processor including a memory; a plurality of sensors; and a transceiver; wherein the plurality of sensors are operable to capture image data, including a plurality of hyperspectral images; wherein the at least one computer processor is operable to automatically perform orthorectification, georectification, radiometric correction, and / or pan sharpening on the image data; wherein the at least one computer processor is operable to fuse the image data; and wherein the transceiver is operable to transmit the fused image data.

2. The artificial satellite of claim 1 , wherein the plurality of sensors include at least one hyperspectral imager, at least one ultraviolet sensor, at least one video imager, at least one infrared spectrometer, and / or at least one automatic identification system.

3. The artificial satellite of claim 1 , wherein the at least one computer processor includes at least one flight processor and at least one payload processor.

4. The artificial satellite of claim 1 , wherein the artificial satellite is included in a constellation of a plurality of other satellites.

5. The artificial satellite of claim 1 , wherein the plurality of hyperspectral images provide for high resolution enhancing of other image data generated by the plurality of sensors.

6. The artificial satellite of claim 1 , wherein the plurality of sensors are operable to capture color video, ultraviolet images, and / or infrared images.

7. The artificial satellite of claim 1 , wherein each of the plurality of sensors are operable to orient towards a common target, and wherein each of the plurality of sensors are operable to obtain the image data from the common target.

8. The artificial satellite of claim 1 , further comprising at least one solar cell operable to power the plurality of sensors and the at least one computer processor.

9. An artificial satellite, comprising: at least one computer processor including a memory; a plurality of sensors; at least one solar cell operable to power the plurality of sensors and the at least one computer processor; and a transceiver; wherein the plurality of sensors are operable to capture image data, including a plurality of hyperspectral images; wherein the at least one computer processor is operable to automatically perform orthorectification, georectification, radiometric correction, and / or pan sharpening on the image data; wherein the at least one computer processor is operable to fuse the image data; and wherein the transceiver is operable to transmit the fused image data.

10. The artificial satellite of claim 9, wherein the plurality of sensors include at least one hyperspectral imager, at least one ultraviolet sensor, at least one video imager, at least one infrared spectrometer, and / or at least one automatic identification system.

11. The artificial satellite of claim 9, wherein the artificial satellite is included in a constellation of a plurality of other satellites.

12. The artificial satellite of claim 9, wherein the at least one computer processor includes at least one flight processor and at least one payload processor.

13. The artificial satellite of claim 12, wherein the at least one flight processor is dedicated to tasks for movement and navigation of the artificial satellite and the at least one payload processor is dedicated to processing tasks related to the plurality of sensors.

14. The artificial satellite of claim 9, wherein the plurality of hyperspectral images provide for high resolution enhancing of other image data generated by the plurality of sensors.

15. The artificial satellite of claim 9, wherein each of the plurality of sensors are operable to orient towards a common target, wherein each of the plurality of sensors are operable to obtain the image data from the common target.

16. The artificial satellite of claim 9, wherein the plurality of sensors are operable to capture color video, ultraviolet images, and / or infrared images.

17. An artificial satellite, comprising: at least one computer processor including a memory; a plurality of sensors; and a transceiver; wherein each of the plurality of sensors are operable to orient towards a common target; wherein the plurality of sensors are operable to capture image data from the common target, the image data including a plurality of hyperspectral images; wherein the at least one computer processor is operable to automatically correct the image data via orthorectification, radiometric correction, and pan sharpening; wherein the at least one computer processor is operable to fuse the image data; and wherein the transceiver is operable to transmit the fused image data.

18. The artificial satellite of claim 17, wherein the plurality of sensors includes a Red, Blue, and Green (RGB) sensor, an optical sensor, two hyperspectral sensors, one automatic identification system, and / or two ultraviolet telescopes.

19. The artificial satellite of claim 17, further comprising at least one solar cell operable to power the plurality of sensors and the at least one computer processor.

20. The artificial satellite of claim 17, wherein the at least one computer processor includes at least one flight processor and at least one payload processor.