Control method of satellite including imaging device

Abstract

A control method of a satellite including a support frame, an optical system installed on the support frame, an imaging module having an image sensor capable of detecting light transmitted from the optical system, a control module having an image processor capable of generating an image using the light detected by the image sensor, and a module support body having one side supporting the imaging module and the other side fixed to the control module according to one embodiment may comprise the operations of: receiving orbit information including information about a plurality of target points sequentially disposed on the orbit of the satellite and a plurality of preheating points respectively corresponding to the plurality of target points; preheating the module support by turning on an electronic component of the satellite when the satellite reaches one preheating point among the plurality of preheating points; and imaging an observation target when the satellite reaches the target point corresponding to the one preheating point among the plurality of target points.

Description

Method for controlling an artificial satellite including an imaging device

[0001] The disclosure below relates to a method for controlling an artificial satellite including an imaging device.

[0002] An artificial satellite is an artificial device launched by a rocket to orbit a planet, and can take images of the Earth using the imaging device mounted on the satellite.

[0003] Imaging devices for satellites typically include multiple optical elements and supporting structures. To achieve the designed optical performance, the fabrication, assembly, and alignment of each component of the imaging device are crucial.

[0004] Meanwhile, the manufacturing, assembly, and alignment of these components can be performed in a clean room at temperatures of approximately 20 degrees. However, actual satellites operate in diverse space environments, making thermal deformation of the structure highly likely. Consequently, image quality may deteriorate as the optical system's focus shifts from the designed position.

[0005] The related art mentioned above is possessed or acquired in the process of deriving the present disclosure and cannot necessarily be said to be prior art disclosed to the general public prior to the filing of the present disclosure.

[0006] In one embodiment, a control method for an artificial satellite including a support frame, an optical system installed on the support frame, an imaging module having an image sensor capable of detecting light transmitted from the optical system, a control module having an image processor capable of generating an image using light detected by the image sensor, and a module supporter having one side supporting the imaging module and the other side fixed to the control module may include: receiving orbital information including information on a plurality of target points sequentially arranged on an orbit of the artificial satellite and a plurality of preheating points respectively corresponding to the plurality of target points; preheating the module supporter by turning on an electronic component of the artificial satellite when the artificial satellite reaches any one of the plurality of preheating points; and photographing an object of observation when the artificial satellite reaches a target point corresponding to any one of the plurality of preheating points.

[0007] According to one embodiment, the method for controlling the artificial satellite may further include: an operation of detecting a temperature of at least one object among the imaging module, the module support, and the control module while performing an operation of photographing the observation object; and an operation of storing the detected temperature when the quality of the image of the photographed observation object does not satisfy a set standard.

[0008] According to one embodiment, the orbital information further includes a plurality of target temperatures each corresponding to the plurality of target points, and the plurality of target temperatures include information on the temperature of the object, and the method for controlling the artificial satellite may further include an operation of increasing or decreasing a time for preheating the module support or correcting the amount of heat per unit time provided to the module support during the time for preheating the module support, depending on a difference between the temperature of the object detected in the detecting operation and the target temperature, when the quality of the image of the photographed observation object does not satisfy a set standard.

[0009] In one embodiment, the preheating operation may include a plurality of heating operations having different heat transfer rates from the electronic component to the module support.

[0010] According to one embodiment, the preheating operation may include a first heating operation for heating the module support by turning ON the image processor; and a second heating operation for heating the module support by turning ON the image sensor while the image processor is ON.

[0011] In one embodiment, the heat transfer rate from the image sensor to the module support may be lower than the heat transfer rate from the image processor to the module support.

[0012] According to one embodiment, the orbital information further includes a plurality of target temperatures each corresponding to the plurality of target points, and the plurality of target temperatures include information about a temperature of at least one object among the imaging module, the module support, and the control module, and the preheating operation may include an operation of detecting a temperature of the object; an operation of turning on an electronic component of the satellite when the temperature of the object is lower than the target temperature; and an operation of turning off an electronic component of the satellite when the temperature of the object is higher than the target temperature.

[0013] According to one embodiment, the control method of the artificial satellite further includes an operation of generating the orbit information, wherein the generating operation includes an operation of receiving the target point and an environmental condition corresponding to the target point; and an operation of determining the preheating point corresponding to each of the target points, wherein the operation of determining the preheating point may include an operation of determining an amount of change in the focal length of the optical system when the support frame is thermally deformed according to the environmental condition; an operation of determining a target temperature of the module support to compensate for the amount of change in the focal length; and an operation of determining an ON time of the electronic component required for the module support to reach the target temperature.

[0014] Figure 1 is a drawing showing an artificial satellite orbiting a planet according to one embodiment.

[0015] FIG. 2 is a drawing showing an imaging device for an artificial satellite according to one embodiment.

[0016] Figure 3 is a block diagram of an artificial satellite according to one embodiment.

[0017] Figure 4 is a flowchart illustrating a method for controlling an artificial satellite according to one embodiment.

[0018] Figure 5 is a flowchart showing a preheating operation according to one embodiment.

[0019] Figure 6 is a flowchart illustrating an operation for generating orbital information according to one embodiment.

[0020] Figure 7 is a graph showing the heat transfer rate according to the operation of an electronic component according to one embodiment.

[0021] FIG. 8 is a drawing showing an imaging device for an artificial satellite according to one embodiment.

[0022] Specific structural or functional descriptions of the embodiments are disclosed for illustrative purposes only and may be modified and implemented in various forms. Therefore, the actual implementation is not limited to the specific embodiments disclosed, and the scope of this specification includes modifications, equivalents, or alternatives included in the technical concepts described in the embodiments.

[0023] Although terms such as "first" or "second" may be used to describe various components, these terms should be interpreted solely to distinguish one component from another. For example, a first component may be referred to as a second component, and similarly, a second component may also be referred to as a first component.

[0024] When it is said that a component is "connected" to another component, it should be understood that it may be directly connected or connected to that other component, but there may also be other components in between.

[0025] Singular expressions include plural expressions unless the context clearly dictates otherwise. In this specification, the terms "comprises" or "has" should be understood to indicate the presence of a described feature, number, step, operation, component, part, or combination thereof, but not to exclude the possibility of the presence or addition of one or more other features, numbers, steps, operations, components, parts, or combinations thereof.

[0026] In this document, each of the phrases "A or B", "at least one of A and B", "at least one of A or B", "A, B, or C", "at least one of A, B, and C", and "at least one of A, B, or C" may include any one of the items listed together in that phrase, or all possible combinations thereof.

[0027] Unless otherwise defined, all terms used herein, including technical or scientific terms, have the same meaning as commonly understood by a person of ordinary skill in the art. Terms defined in commonly used dictionaries should be interpreted to have a meaning consistent with their meaning in the context of the relevant technology, and will not be interpreted in an idealized or overly formal sense unless explicitly defined herein.

[0028] Hereinafter, embodiments will be described in detail with reference to the attached drawings. In the description with reference to the attached drawings, identical components are assigned the same reference numerals regardless of the drawing numbers, and redundant descriptions thereof will be omitted.

[0029] Components included in one embodiment and components with common functions will be described using the same names in other embodiments. Unless otherwise stated, the descriptions given in one embodiment may also apply to other embodiments, and detailed descriptions will be omitted to the extent of overlap.

[0030]

[0031] Figure 1 is a drawing showing an artificial satellite orbiting a planet according to one embodiment.

[0032] Referring to FIG. 1, an artificial satellite (A) according to one embodiment may orbit along a set orbit around a planet (E) (e.g., Earth). The artificial satellite (A) may include an imaging device for photographing the planet (E) or a space environment. The imaging device may include a plurality of optical elements and an image sensor for detecting light received therethrough. In order to improve the quality of an image captured by the imaging device, the image sensor may be arranged in consideration of a focal length determined according to the shape and positional relationship of the plurality of optical elements.

[0033] Meanwhile, the artificial satellite (A) is subjected to diverse and extreme space environments. For example, the temperatures can differ significantly when the artificial satellite (A) is located close to the sun (S) and when the artificial satellite (A) is located in the umbra region, which is located on the opposite side of the sun (S) from the planet (E). In this process, thermal deformation of the structure of the artificial satellite (A) can easily occur, which causes a shift in the focal position of the imaging device, potentially degrading the quality of the image captured using the imaging device. Therefore, to prevent such deterioration of image quality, a means of adjusting the focal length is required.

[0034]

[0035] FIG. 2 is a drawing showing an imaging device for an artificial satellite according to one embodiment.

[0036] Referring to FIG. 2, an imaging device (1) for an artificial satellite according to one embodiment may include a support frame (11), an optical system (12, 13), an imaging module (14), a control module (15), a module support (16), and wiring (17).

[0037] The support frame (11) is configured to be fixed to internal components of an imaging device (1) for an artificial satellite and to support the internal components. The support frame (11) may be directly connected to each internal component, or indirectly connected to another internal component through one internal component. For example, the support frame (11) may be directly connected to the optical system (12, 13) and the control module (15), and may not be directly connected to the imaging module (14) and the module support (16). For example, the primary mirror (12) of the optical system (12, 13) may be installed on one side of the support frame (11), the control module (15) may be installed on the other side, and the secondary mirror (13) of the optical system (12, 13) may be installed on a portion of the support frame (11) located between the primary mirror (12) and the control module (15). The support frame (11) may be formed of a material having a low coefficient of thermal expansion to reduce changes in the distance between internal components directly connected to the support frame (11) due to heat. For example, the coefficient of thermal expansion of the support frame (11) may be 2.0 x 10 -6 / ℃ can be formed of a material smaller than that. For example, the support frame (11) can be formed of invar (e.g., invar 36). With this configuration, even when the module support (16) is thermally deformed as described below, the change in the distance between internal components directly connected to the support frame (11) can be reduced. Meanwhile, although FIG. 2 exemplarily illustrates a case in which the support frame (11) is integrally formed as a single component, it should be noted that the support frame (11) may be formed by assembling or welding a plurality of components. It should be noted that the specific shape and structure of the support frame (11) are not limited unless otherwise stated.

[0038] The optical system (12, 13) can refract and / or reflect light transmitted from space and transmit it to the imaging module (14). The optical system (12, 13) can be installed on the support frame (11). For example, the optical system (12, 13) can include a primary mirror (12) that reflects light incident from the outside, and a secondary mirror (13) that re-reflects the light reflected by the primary mirror (12) toward the imaging module (14). For example, the primary mirror (12) can be arranged closer to the imaging module (14) than the secondary mirror (13). Meanwhile, it should be noted that the optical system (12, 13) does not have to be composed of only the primary mirror (12) and the secondary mirror (13). For example, the optical system (12, 13) may further include at least one optical element arranged between the secondary mirror (13) and the imaging module (14). For example, it is noted that the optical system (12, 13) may include at least one optical element (e.g., a lens) that refracts light instead of having a reflector.

[0039] The imaging module (14) may include an image sensor (141, see FIG. 3) that detects light transmitted from the optical system (12, 13). According to one embodiment, when taking a picture using the imaging device (1), the image quality can be improved by positioning the image sensor (141) at the focal length of the optical system (12, 13). For example, the imaging module (14) may not be directly connected to the support frame (11), but may be indirectly connected to the support frame (11) through the module support (16). With this configuration, when the focal length of the optical system (12, 13) changes due to thermal deformation of the support frame (11), the position of the image sensor (141) can be adjusted by applying heat to the module support (16) so that the image sensor (141) is positioned to match the changed focal length of the optical system (12, 13). Meanwhile, when the module support (16) expands due to heat, the image sensor (141) moves in a direction approaching the optical system (12, 13). In addition, since space generally has a lower temperature than room temperature, the image sensor (141) can be placed at a position further away from the optical system (12, 13) than the focal length of the optical system (12, 13) based on room temperature.

[0040] The control module (15) may be equipped with an image processor (152, see FIG. 3) capable of generating an image using light detected by the image sensor (141). The image processor (152) may be, for example, an FPGA (field programmable gate array), but is not limited thereto. The control module (15) may heat the module support (16) by turning on electronic components (e.g., the image processor (152) and / or the image sensor (141)) provided in the imaging device (1). Here, the electronic components are components arranged adjacent to the module support (16), and may include the image processor (152) provided in the control module (15) and the image sensor (141) included in the imaging module (14). For example, the imaging device (1) may not be equipped with a heater that provides a higher amount of heat per unit time to the module support (16) than the image sensor (141) and the image processor (152). For example, a component (e.g., a resistance heating wire) that generates more heat per unit time than the image sensor (141) may not be provided between the module support (16) and the image sensor (141). For example, a component (e.g., a resistance heating wire) that generates more heat per unit time than the image processor (152) may not be provided between the module support (16) and the image processor (152).

[0041] According to one embodiment, the module support (16) can be heated or cooled only by using the ON or OFF operation of the electronic components provided for image capturing, without having a separate heater or constant temperature system. In other words, the position of the image sensor (141) can be adjusted by controlling the operation of the electronic components provided for image capturing, without having a separate heater or mechanical focus adjustment stage. According to this configuration, it becomes possible to adjust the position of the image sensor (141) even in an imaging device (1) mounted on a small satellite, such as a cube satellite, which is known to be difficult to adjust the focal length. In addition, even if it is not a small satellite, since there is no need to have a separate means for focus adjustment, the volume and weight of the imaging device (1) or the artificial satellite (A) mounted thereon can be reduced. Meanwhile, it is known that the sensitivity of focus adjustment is typically high in the order of positional change of the primary mirror (12), positional change of the secondary mirror (13), and positional change of the image sensor (141). Therefore, as in one embodiment, when the position of the image sensor (141) is utilized as a focus adjustment factor, there is an advantage in that the focus can be adjusted more precisely.

[0042] One side of the module support (16) supports the imaging module (14), and the other side of the module support (16) can be fixed to the control module (15). The thermal expansion coefficient of the module support (16) can be higher than the thermal expansion coefficient of the support frame (11). According to this configuration, as described above, in the imaging device (1), even when the structure supporting the optical system (12, 13) is deformed (e.g., contracted or expanded) due to environmental influences and the focus position of the optical system (12, 13) deviates from the position of the image sensor (141), the image sensor (141) can be corrected to be positioned at the changed focus by thermally deforming the module support (16) supporting the image sensor (141). For example, the thermal expansion coefficient of the module support (16) can have a value that is 100 times or more larger than the thermal expansion coefficient of the support frame (11). For example, the thermal expansion coefficient of the module support (16) is 20.0 x 10 -6 / ℃ may be greater than. For example, the module support (16) may be formed of aluminum (e.g., Al6082-T6).

[0043] The wiring (17) can interconnect the imaging module (14) and the control module (15). For example, the length of the wiring (17) can be formed longer than the distance between the imaging module (14) and the control module (15) based on room temperature. With this structure, even when the module support (16) is thermally deformed, the problem of the wiring (17) being damaged due to tension being applied to the wiring (17) can be reduced. For example, the wiring (17) can be formed of a flexible material so that its shape can change in response to changes in the volume of the module support (16) depending on the ambient temperature. For example, the wiring (17) can be formed of a flexible printed circuit board (FPCB). With this configuration, the problem of the wiring (17) being damaged by external force can be reduced even when the distance between the imaging module (14) and the control module (15) changes due to repeated thermal deformation of the module support (16).

[0044]

[0045] Figure 3 is a block diagram of an artificial satellite according to one embodiment.

[0046] Referring to FIG. 3, an artificial satellite according to one embodiment may include a processor (P), an image sensor (141), a memory (22), a communication module (24), and a temperature sensor (25).

[0047] The processor (P) can receive information from one or more electronic components (e.g., 22, 24, 25, 141) connected to the processor (P), transmit the information to one or more other electronic components (e.g., 22, 24, 25, 141), or control one or more other electronic components (e.g., 22, 24, 25, 141). For example, the processor (P) can turn on or off the image sensor (141). The processor (P) can include, for example, a main processor (21) and an image processor (152).

[0048] The main processor (21) can transmit and receive signals with other processors, including the image processor (152). The main processor (21) can turn the image processor (152) on or off depending on whether the operation of the image processor (152) is necessary. The main processor (21) (210) can determine whether the quality of the image formed by the image processor (152) satisfies a set standard (e.g., relative edge resolution (REP), point spread function (PSF) and / or modulation transfer function (MTF) conditions). For example, the main processor (21) may be installed in another component spaced apart from the control module (15) (15, see FIG. 2) where the image processor (152) is located, but is not limited thereto.

[0049] The image processor (152) can generate an image based on information collected from the image sensor (141). The image processor (152) can turn the image sensor (141) on or off. When the image processor (152) is turned on, heat generated from the image processor (152) can be transferred to the module support (16) (16, see FIG. 2). In addition, when the image sensor (141) is turned on while the image processor (152) is turned on, higher heat can be transferred to the module support (16).

[0050] Meanwhile, although the main processor (21) and the image processor (152) have been described separately and their respective functions have been described, it should be noted that the above-described functions may be performed by a single processor. In addition, it should be noted that some or all of the functions performed by the main processor (21) may be performed by an external electronic device (e.g., a terminal located on the ground or another artificial satellite (A) located in space).

[0051] In the memory (22), images collected from the image sensor (141), information received through the input module (23) or the communication module (24), and the temperature measured by the temperature sensor (25) can be stored. In the memory (22), criteria for evaluating the quality of images generated by the image processor (152) and orbital information of the artificial satellite (A) can be stored.

[0052] Here, the orbital information may include environmental conditions (e.g., ambient temperature) of points located on the orbit of the artificial satellite (A). The orbital information may include information on a plurality of target points sequentially arranged on the orbit of the artificial satellite (A) and a plurality of preheating points corresponding to each of the plurality of target points.

[0053] Here, the target point can be understood to mean the position of the artificial satellite (A) where the shooting using the imaging device (1) is to be performed. Meanwhile, in order to make the position of the image sensor (141) at the target point match the focal length of the optical system, it is necessary to heat the module support (16) in advance before reaching the target point. For example, by heating the module support (16) from a point in time prior to reaching the target point or from when the artificial satellite (A) has reached a position in the orbit prior to that, the position of the image sensor (141) can be made to match the focal length of the optical system. The point in time or position at which the module support (16) should begin to be heated in this way can be referred to as a preheating point. An exemplary method for determining such a preheating point will be described later with reference to FIG. 6.

[0054] The communication module (24) can support the establishment of a wireless communication channel between an artificial satellite (A) and an external electronic device (e.g., a terminal located on the ground or another artificial satellite (A) located in space), and the performance of communication through the established communication channel. For example, the communication module (24) can transmit information collected from various sensors such as an image sensor (141) and a temperature sensor (25), information stored in a memory (22), or information determined by a processor (P) to an external electronic device. For example, the communication module (24) can receive orbital information from an external electronic device. The processor (P) can update the orbital information of the memory (22) based on the information received from the communication module (24).

[0055] The temperature sensor (25) can detect the temperature of an object located inside an artificial satellite (A). Here, the object may include at least one of an imaging module (14), a module support (16), and a control module (15). The information detected by the temperature sensor (25) can be utilized to correct the on and off times of an image processor (152) or an image sensor (141), as described below.

[0056]

[0057] Figure 4 is a flowchart illustrating a method for controlling an artificial satellite according to one embodiment.

[0058] Referring to FIG. 4, a method for controlling an artificial satellite according to an embodiment may include an operation of inputting orbital information (410), an operation of measuring position information of an artificial satellite (420), an operation of determining whether a preheating point has been reached (430), an operation of preheating a module support (16) (440), an operation of determining whether an artificial satellite has reached a target point (450), an operation of photographing an observation target (460), an operation of detecting a temperature of an object (470), an operation of determining whether an image quality satisfies a set standard (480), and an operation of modifying a preheating condition (490).

[0059] In operation 410, the orbital information may include information about a plurality of target points sequentially arranged on the orbit of the satellite and a plurality of preheating points corresponding to each of the plurality of target points. For example, the orbital information may be stored in advance in the memory (22) prior to the flight of the satellite. For example, the orbital information may be received from an external electronic device via the communication module (24) while the satellite is in flight.

[0060] In operation 420, position information of an artificial satellite can be measured. For example, the position of an artificial satellite can be measured through a positioning system mounted on the artificial satellite, or can be received from an external electronic device through a communication module (24).

[0061] In operation 430, if the position of the artificial satellite has not reached the preheating point, operation 420 may be repeatedly performed. In operation 430, if the position of the artificial satellite has reached the preheating point, operation 440 may be performed.

[0062] In operation 440, when the satellite reaches any one of the plurality of preheating points, the module support (16) may be preheated by turning on electronic components of the satellite. For example, operation 440 may include a plurality of heating operations having different heat transfer rates from electronic components (e.g., the image processor (152) and / or the image sensor (141)) to the module support (16). Operation 440 may include a first heating operation of heating the module support (16) by turning on the image processor (152), and a second heating operation of heating the module support (16) by turning on the image sensor (141) while the image processor (152) is turned on.

[0063] In the first heating operation, the main processor (21) can turn on the image processor (152). When the image processor (152) is turned on, the module support (16) can be heated by the heat generated from the image processor (152). In the second heating operation, the image processor (152) can turn on the image sensor (141). When the image sensor (141) is turned on while the image processor (152) is turned on, higher heat can be transferred to the module support (16). For example, it should be noted that operation 440 can be continuously performed until the position of the artificial satellite reaches the target point, but is not limited thereto.

[0064] In operation 460, when the artificial satellite reaches a target point corresponding to one of the preheating points among the plurality of target points, the imaging device (1) for the artificial satellite can photograph the observation target. The image processor (152) can drive the image sensor (141) to photograph the observation target. In this case, a higher heat than when the image sensor (141) is turned on can be transferred to the module support (16).

[0065] Meanwhile, while performing the operation (460) of photographing the observation target, operation 470 may be performed. In operation 470, the temperature sensor (25) may detect the temperature of at least one of the objects among the imaging module (14), the module support (16), and the control module (15).

[0066] In operation 480, if the quality of the image of the photographed observation target satisfies the set criteria, operations 420 to 470 may be repeated according to the target point after the target point reached just before and the corresponding preheating point. Here, the set criteria for measuring the quality of the image may be determined, for example, according to whether the quality of the photographed image satisfies REP (relative edge resolution), PSF (point spread function) and / or MTF (modulation transfer function) conditions.

[0067] In operation 480, if the quality of the image of the captured observation target does not meet the set criteria, the temperature detected by the temperature sensor (25) may be stored. For example, the user may modify the orbit information based on the temperature stored in operation 480 and the captured image. For example, the temperature stored in operation 480 and the captured image may be analyzed by the user after the satellite returns to the ground, or may be provided to the user via the communication module (24) during the satellite's flight. In this way, by inputting the orbit information modified by the user into the satellite, the preheating condition for the module support (16) may be modified (490). As another example, in operation 490, the processor (P) (e.g., the main processor (21)) may automatically modify the orbit information without user intervention.

[0068] For example, if the quality of the image of the photographed observation target does not meet the set standard as a result of performing operation 480, and the stored temperature does not reach the set target temperature, it can be seen that the image sensor (141) is located further away from the optical system than the focal length of the optical system at the time of photographing. Accordingly, the preheating condition can be modified in the direction in which a higher amount of heat is provided to the module support (16). Meanwhile, the target temperature can be understood as the temperature of the object that brings the image sensor (141) to a position corresponding to the focal length when the artificial satellite reaches the target point. An exemplary method for determining such a target temperature will be described later with reference to FIG. 6. The orbit information may include a plurality of target temperatures each corresponding to a plurality of target points.

[0069] As an example of a method for providing a higher amount of heat to the module support (16), the preheating time for the module support (16) can be increased by advancing the preheating point at which the image processor (152) is turned on. In other words, the distance between the plurality of preheating points corresponding to the plurality of target points can be corrected. As another example, the amount of heat transferred per unit time to the module support (16) can be increased by advancing the time at which the image sensor (141) is turned on while the image processor (152) is turned on. In operation 490, the processor (P) can increase the preheating time for the module support (16) or increase the amount of heat per unit time provided to the module support (16) during the time of preheating the module support (16) in proportion to the difference between the temperature of the object detected in operation (470) of detecting the temperature of the object when the quality of the image of the captured observation object does not satisfy the set standard.

[0070] Conversely, if the quality of the image of the captured observation object does not meet the set standard as a result of performing operation 480 and the stored temperature exceeds the set target temperature, it can be seen that the image sensor (141) is positioned closer to the optical system than the focal length of the optical system at the time of shooting. Accordingly, the preheating conditions can be modified in a direction in which a lower amount of heat is provided to the module support (16), and a detailed description thereof will be omitted.

[0071] For example, the preheat conditions modified through operation 490 may be applied the next time the satellite approaches the same target point.

[0072]

[0073] Figure 5 is a flowchart showing a preheating operation according to one embodiment.

[0074] Referring to FIG. 5, a preheating operation (440) according to an embodiment may include an operation (441) of detecting a temperature of a target object, an operation (442) of determining whether the temperature of the target object is higher than a target temperature based on orbital information, an operation (443) of turning off electronic components of a satellite if the temperature of the target object is higher than the target temperature based on orbital information, and an operation (444) of turning on electronic components of the satellite if the temperature of the target object is lower than the target temperature. Here, the orbital information may include a plurality of target temperatures each corresponding to a plurality of target points. The plurality of target temperatures may include information on the temperature of at least one of the imaging module, the module support, and the control module.

[0075] Unlike the explanation in FIG. 4 that the preheating operation (440) is continuously performed until the artificial satellite reaches the target point, it is to be noted that the preheating operation (440) may be performed through feedback control using a temperature sensor (25), as illustrated in FIG. 5.

[0076]

[0077] Figure 6 is a flowchart illustrating an operation for generating orbital information according to one embodiment.

[0078] Referring to FIG. 6, the operation of generating orbital information according to one embodiment may include an operation (610) of receiving a target point and environmental conditions, and an operation (620) of determining a preheating point corresponding to each target point. The following describes an example in which the operation of generating orbital information is performed through a test or simulation on the ground, but it should be noted that, unless otherwise stated, it may also be performed through a computing device mounted on the artificial satellite itself.

[0079] In operation 610, information about target points and environmental conditions corresponding to the target points (e.g., ambient temperature) may be input into a computing device for testing or simulation.

[0080] Action 620 may include an action (621) of determining a focal length change amount according to environmental conditions, an action (622) of determining a target temperature of the module support (16), and an action (623) of determining an ON time of an electronic component for reaching the target temperature.

[0081] In operation 621, the amount of focal length change depending on environmental conditions can be determined through simulation or ground testing. For example, when an artificial satellite is installed in a thermal vacuum chamber, the amount of focal length change can be measured while varying the temperature within the thermal vacuum chamber depending on environmental conditions. Through operation 621, the amount of focal length change of the optical system when the support frame (11, see FIG. 2) is thermally deformed depending on environmental conditions can be determined.

[0082] In operation 622, a target temperature of the module support (16) can be determined to compensate for the change in focal length. At the target temperature, the module support (16) is thermally deformed, thereby allowing the image sensor (141, see FIG. 3) to be positioned at a position where the aforementioned change in focal length is compensated for, i.e., at a position corresponding to the focal length of the optical system.

[0083] In operation 623, the ON time of the electronic components required for the module support (16) to reach the target temperature can be determined. For example, the ON time of the image processor (152, see FIG. 3) and the ON time of the image sensor (141) can each be determined. For example, it should be noted that the image sensor (141) may be determined as a point in time after a certain period of time has elapsed from the ON time of the image processor (152).

[0084] A preheating point may be determined based on the ON time of the electronic component determined through operations 621 to 623. For example, the preheating point may be expressed as positional information or time information. For example, the preheating point may be determined as a time preceding the preheating time based on the expected time of reaching the target point. For example, the preheating point may be determined as a location preceding the target point, taking into account the flight speed and preheating time of the artificial satellite while approaching the target point.

[0085]

[0086] Figure 7 is a graph showing the heat transfer rate according to the operation of an electronic component according to one embodiment.

[0087] Referring to FIG. 7, a preheating section (P1) in which an operation of preheating a module support (16) is performed (440, see FIG. 4), a shooting section (P2) in which an operation of shooting an observation target (450, see FIG. 4) is performed, and a processing section (P3) in which shooting is completed and image processing is performed in an image processor (152) are illustrated.

[0088] In the preheating section (P1), the image processor (152, see FIG. 3) may be turned on at a first time point (t1) when the preheating point is first reached, and the image sensor (141, see FIG. 3) may be turned on at a second time point (t2) while the image processor (152) is turned on. In a state where both the image processor (152) and the image sensor (141) are turned on, the amount of heat per unit time transferred to the module support (16, see FIG. 2) may be higher than in a state where only the image processor (152) is turned on.

[0089] In the shooting section (P2), the observation object can be captured at the third time point (t3) to the fourth time point (t4) upon reaching the target point. In the shooting section (P2) where actual shooting is performed, a higher amount of heat can be supplied to the module support (16) than in the preheating section (P1) where the image sensor (141) and the image processor (152) are turned on and waiting. Meanwhile, the shooting section (P2) can be sufficiently shorter than the preheating section (P1).

[0090] In the processing section (P3), the image sensor (141) is turned off, and the image processor (152) remains on until the image processing task is completed, and can then be turned off.

[0091] For example, the heat transfer rate (H1) transferred from the image sensor (141) to the module support (16) may be lower than the heat transfer rate (H2-H1) transferred from the image processor (152) to the module support (16). With this configuration, the temperature of the module support (16) can be adjusted to accurately reach the target temperature using the image sensor (141) while the module support (16) is quickly heated to a specific temperature lower than the target temperature using the image processor (152). For example, when the image processor (152) is turned on, the amount of heat transferred to the module support (16) can be precisely controlled by selectively turning on or off the image sensor (141) having a relatively low heat transfer rate.

[0092]

[0093] FIG. 8 is a drawing showing an imaging device for an artificial satellite according to one embodiment.

[0094] Referring to FIG. 8, an imaging device (1) for an artificial satellite according to one embodiment may include a support frame (11), an optical system (12, 13), an imaging module (14), a control module (15), a module support (16), and wiring (17).

[0095] For example, the support frame (11) may be directly connected to the optical system (12, 13) and the control module (15), and may not be directly connected to the imaging module (14) and the module support (16). As described above, although the support frame (11) is exemplarily illustrated as being integrally formed as a single component, it should be noted that the support frame (11) may alternatively be formed by assembling or welding a plurality of components. Unless otherwise stated, it should be noted that the specific shape and structure of the support frame (11) are not limited.

[0096]

[0097] The embodiments described above may be implemented using hardware components, software components, and / or a combination of hardware components and software components. For example, the devices, methods, and components described in the embodiments may be implemented using a general-purpose computer or a special-purpose computer, such as, for example, a processor, a controller, an arithmetic logic unit (ALU), a digital signal processor, a microcomputer, a field programmable gate array (FPGA), a programmable logic unit (PLU), a microprocessor, or any other device capable of executing instructions and responding to them. The processing device may execute an operating system (OS) and software applications running on the operating system. The processing device may also access, store, manipulate, process, and generate data in response to the execution of the software. For ease of understanding, the processing device is sometimes described as being used alone; however, one of ordinary skill in the art will recognize that the processing device may include multiple processing elements and / or multiple types of processing elements. For example, a processing unit may include multiple processors, or a processor and a controller. Other processing configurations, such as parallel processors, are also possible.

[0098] Software may include a computer program, code, instructions, or a combination of one or more of these, and may configure a processing device to perform a desired operation or, independently or collectively, command the processing device. The software and / or data may be permanently or temporarily embodied in any type of machine, component, physical device, virtual equipment, computer storage medium or device, or transmitted signal wave for interpretation by the processing device or for providing instructions or data to the processing device. The software may also be distributed over networked computer systems and stored or executed in a distributed manner. The software and data may be stored on a computer-readable recording medium.

[0099] The method according to the embodiment may be implemented in the form of program commands that can be executed through various computer means and recorded on a computer-readable medium. The computer-readable medium may store program commands, data files, data structures, etc., alone or in combination, and the program commands recorded on the medium may be those specially designed and configured for the embodiment or may be known and available to those skilled in the art of computer software. Examples of the computer-readable recording medium include magnetic media such as hard disks, floppy disks, and magnetic tapes, optical media such as CD-ROMs and DVDs, magneto-optical media such as floptical disks, and hardware devices specially configured to store and execute program commands such as ROMs, RAMs, and flash memories. Examples of program commands include not only machine language codes such as those generated by a compiler, but also high-level language codes that can be executed by a computer using an interpreter, etc.

[0100] The hardware device described above may be configured to operate as one or more software modules to perform the operations of the embodiment, and vice versa.

[0101]

[0102] Although the embodiments described above have been described with limited drawings, those skilled in the art will appreciate that various technical modifications and variations can be applied based on the described embodiments. For example, appropriate results can still be achieved even if the described techniques are performed in a different order than described, and / or components of the described systems, structures, devices, circuits, etc. are combined or combined in a different manner than described, or are replaced or substituted with other components or equivalents.

[0103] Therefore, other implementations, other embodiments, and equivalents to the claims also fall within the scope of the claims described below.

Claims

1. A method for controlling an artificial satellite, comprising: a support frame; an optical system installed on the support frame; an imaging module having an image sensor capable of detecting light transmitted from the optical system; a control module having an image processor capable of generating an image using light detected by the image sensor; and a module supporter having one side supporting the imaging module and the other side fixed to the control module, wherein the control method comprises: An operation of receiving orbital information including information on a plurality of target points sequentially arranged on the orbit of the artificial satellite and a plurality of preheating points corresponding to each of the plurality of target points; An operation of preheating the module support by turning on the electronic components of the satellite when the satellite reaches any one of the plurality of preheating points; and When the artificial satellite reaches a target point corresponding to one of the plurality of target points, the operation of photographing the observation target is included. Method of controlling an artificial satellite.

2. In paragraph 1, The above method of controlling the artificial satellite is as follows: An operation of detecting the temperature of at least one object among the imaging module, the module support, and the control module while performing an operation of photographing the observation object; and If the quality of the image of the above-described photographed observation target does not satisfy the set standard, further comprising an operation of storing the detected temperature. Method of controlling an artificial satellite.

3. In paragraph 2, The above orbital information further includes a plurality of target temperatures corresponding to each of the plurality of target points, The above plurality of target temperatures include information about the temperature of the object, The above method of controlling the artificial satellite is as follows: If the quality of the image of the above-mentioned photographed observation object does not satisfy the set standard, the operation of increasing or decreasing the time for preheating the module support or correcting the amount of heat per unit time provided to the module support during the time for preheating the module support is further included, depending on the difference between the temperature of the object detected in the above-mentioned sensing operation and the target temperature. Method of controlling an artificial satellite.

4. In paragraph 1, The above preheating operation includes a plurality of heating operations having different heat transfer rates from the electronic component to the module support. Method of controlling an artificial satellite.

5. In paragraph 4, The above preheating action is, A first heating operation for heating the module support by turning on the image processor; and Including a second heating operation for heating the module support by turning on the image sensor while the image processor is turned on. Method of controlling an artificial satellite.

6. In paragraph 5, The heat transfer rate from the image sensor to the module support is lower than the heat transfer rate from the image processor to the module support. Method of controlling an artificial satellite.

7. In paragraph 1, The above orbital information further includes a plurality of target temperatures corresponding to each of the plurality of target points, The plurality of target temperatures include information about the temperature of at least one object among the imaging module, the module support, and the control module, The above preheating action is, An action of detecting the temperature of the above object; If the temperature of the object is lower than the target temperature, an operation of turning on the electronic components of the artificial satellite; and If the temperature of the object is higher than the target temperature, an action is included to turn off the electronic components of the artificial satellite. Method of controlling an artificial satellite.

8. In paragraph 1, The above method of controlling the artificial satellite further includes an operation of generating the orbital information, wherein the generating operation comprises: An operation of receiving the target point and environmental conditions corresponding to the target point; and Including an operation of determining the preheating points corresponding to each of the target points, The action of determining the above preheating point is: An operation for determining the amount of change in the focal length of the optical system when the support frame is thermally deformed according to the environmental conditions; An operation for determining a target temperature of the module support to compensate for the change in the focal length; and The module support includes an operation for determining the ON time of the electronic component required to reach the target temperature. Method of controlling an artificial satellite.

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