Multi-sensor integrated observation apparatus and method for spaceborne payload for acquisition of heterogeneous images

Abstract

The present invention provides an observation device capable of being mounted on a satellite, comprising: a payload capable of being mounted on a satellite body; an imaging radar unit capable of transmitting and receiving radio waves and installed on the payload; and an electro-optical / infrared unit capable of receiving light / thermal radiation and installed on the payload in the same direction as the imaging radar unit transmits and receives radio waves; and an observation method applicable thereto, wherein the observation device and observation method are capable of being mounted on a satellite to improve observation efficiency.

Description

Technology Field

[0001] The present invention relates to a multi-sensor integrated observation device and observation method for a satellite payload, and more specifically, to an observation device and observation method capable of improving observation efficiency through heterogeneous image acquisition by mounting an electro-optical (EO) / infrared (IR) / synthetic aperture radar (SAR) integrated sensor on a single satellite. Background Technology

[0003] Examples of ground observation equipment operated in space include imaging radar payloads and electro-optical / infrared payloads. Imaging radar payloads observe the ground and ocean from space. Specifically, imaging radar payloads transmit radio waves from space to the ground and ocean, receive waves reflected from them, and process the minute time and phase differences of the reflected waves to create high-resolution images, from which they observe the surface. Electro-optical / infrared payloads receive light and heat emitted from the ground and ocean, and process the received light and heat to detect and track targets on the ground and ocean.

[0004] However, satellites are generally equipped with a single type of observation instrument. More specifically, electro-optical / infrared sensors and imaging radar sensors are mounted on and operated on individual satellites. Consequently, each satellite can acquire only limited information corresponding to the type of observation instrument it carries out and can perform missions based only on that limited information. This presents significant limitations in terms of cost-effectiveness and efficiency in satellite operations. Furthermore, acquiring heterogeneous imagery of the same region faces limitations in timeliness due to the time lag caused by the operation of individual satellites.

[0005] The technology forming the background of the present invention is disclosed in the following patent documents. Prior art literature

[0006] (Patent Document 0001) KR 10-2673504 B1(Patent Document 0002) KR 10-2025-0083712 A The problem to be solved

[0007] The present invention provides a multi-sensor integrated observation device and observation method for a satellite payload that can improve observation efficiency through heterogeneous image acquisition. means of solving the problem

[0008] An observation device according to an embodiment of the present invention comprises: an observation device that can be mounted on a satellite, wherein the observation device comprises: a payload unit that can be mounted on a satellite body; an imaging radar unit that can transmit and receive radio waves and is installed on the payload unit; and an electro-optical / infrared unit that can receive light / heat and is installed on the payload unit in the same direction as the imaging radar unit transmits and receives radio waves.

[0009] The above imaging radar unit is arranged in one direction, and the electro-optical / infrared unit may have its center aligned in one direction with the center of the imaging radar unit, or may be spaced from the center of the imaging radar unit in the other direction by the size of the aperture of the electro-optical / infrared unit in a direction intersecting the one direction, so as to minimize shielding by the imaging radar unit.

[0010] The above imaging radar unit may include: a feeder unit in which the electro-optical / infrared unit can be aligned or overlapped; a reflector unit disposed along the periphery of the feeder unit for reflecting radio waves; and a deployment unit for deploying the reflector unit around the feeder unit.

[0011] The reflective part may include a mesh form or a carbon fiber reinforced composite (CFRP) material, and the unfolding part may include a material that can be elastically bent and unfolded in at least a portion, or may include a cable and a motor.

[0012] The feeder portion comprises: a support member extending in one direction from one side of the mounting portion; a feeder disposed at the end of the support member; and a connecting member supporting the feeder on the support member. The electro-optical / infrared portion may be aligned with the feeder and the connecting member in the one direction, or disposed to be offset from the feeder and the connecting member in another direction that intersects the one direction.

[0013] The feeder portion comprises: a support member extending in one direction from one side of the mounting portion; a sub-reflector member disposed at the end of the support member and supported by the support member; a feeder spaced apart from the sub-reflector member toward one side of the mounting portion; and a connecting member that supports the feeder on the support member or the sub-reflector member, wherein the electro-optical / infrared portion may be disposed to move away from the sub-reflector member in another direction that is a direction intersecting with the one direction.

[0014] The above feeder may include a horn antenna.

[0015] The above image radar unit may further include an RF amplifier connected to the feeder.

[0016] The above RF amplifier may include a semiconductor (GaN) power amplifier (SSPA) or a traveling wave tube amplifier (TWTA).

[0017] The electro-optical / infrared section may include: a tube extending in the one direction and having an interior open in the one direction so that light / heat can be incident thereon, and disposed on one side of the mounting section; a main reflector having a hole in its center, installed facing the direction in which light / heat is incident on the other end of the tube, between one end of the tube near the end of the support member and the other end of the tube far from the end of the support member; a secondary reflector disposed on the one end of the tube to face the main reflector and aligned with the main reflector in the one direction; and a radial support member extending radially from one end of the tube toward the secondary reflector to support the secondary reflector on the tube.

[0018] The electro-optical / infrared part is aligned in one direction with the feeder and the connecting member, and to minimize shielding, the radial support member is aligned in one direction with the connecting member, overlaps in the other direction, and can be radially aligned with the support member.

[0019] An observation method according to an embodiment of the present invention comprises: a process of launching a satellite body equipped with an imaging radar unit capable of transmitting and receiving radio waves and an electro-optical / infrared unit capable of receiving light / heat into space and positioning it in orbit; a process of transmitting and receiving radio waves through the imaging radar unit; a process of receiving light / heat through the electro-optical / infrared unit; and a process of generating single or heterogeneous information for the same observation area using at least one of the transmitted and received radio waves and the received light / heat.

[0020] Depending on the time elapsed and weather conditions of the above-mentioned monitoring area, only transmitted and received radio waves may be used, only received light / heat may be used, or transmitted and received radio waves and received light / heat may be combined and used.

[0021] While transmitting and receiving radio waves through the above-mentioned imaging radar unit, light / heat is received through the above-mentioned electro-optical / infrared unit, and heterogeneous information regarding the same observation area can be simultaneously generated using at least one of the received light / heat and the transmitted and received radio waves.

[0022] The process of generating information about the observation area may further include: a process of generating first information by signal processing the radio waves; a process of generating second information by image processing the light / heat; and a process of generating merged information by merging the first information and the second information, and outputting the merged information as observation information.

[0023] Between the process of launching the satellite body into space and positioning it in orbit and the process of transmitting and receiving radio waves through the imaging radar unit, the process of deploying the reflector of the imaging radar unit, which can reflect radio waves and be folded and unfolded; and the process of transmitting and receiving radio waves through the imaging radar unit may include the process of transmitting and receiving radio waves through the feeder of the imaging radar unit located at the center of the reflector.

[0024] The process of receiving light / heat through the above-mentioned electro-optical / infrared section may include: a process of introducing light / heat into the body of the electro-optical / infrared section, the center of which is aligned with the feeder section; a process of reflecting light / heat in the order of the main reflector and the sub-reflector of the electro-optical / infrared section disposed within the body; and a process of minimizing shielding of light / heat incident on the main reflector by utilizing the alignment state between the radial connecting member supporting the sub-reflector and the feeder section.

[0025] The process of receiving light / heat through the above-mentioned electro-optical / infrared section may include: a process of introducing light / heat into the body of the electro-optical / infrared section, which is spaced apart from the feeder section by the aperture size of the electro-optical / infrared section; and a process of reflecting light / heat in the order of the main reflector and the sub-reflector of the electro-optical / infrared section disposed within the body.

[0026] The above satellite may include a small satellite. Effects of the invention

[0027] According to an embodiment of the present invention, by mounting an observation device comprising an imaging radar unit and an electro-optical / infrared unit on a satellite, the satellite can acquire both imaging radar information and electro-optical / infrared information regarding the same observation area in the same orbit at the same time whenever the observation device operates (e.g., taking a picture). Therefore, identification and judgment of ground targets within the observation area can be facilitated, and accurate information about the targets can be quickly provided to the satellite operator. This enables reliable observation performance and improves observation efficiency. Furthermore, the mission of acquiring imaging radar information and the mission of acquiring electro-optical / infrared information can be performed by a single satellite. As such, since a single satellite can perform different missions, the number of satellites operating in orbit for mission execution can be reduced, and consequently, the role of the ground station can be reduced, thereby allowing for the efficient utilization of satellite and ground station infrastructure. Brief explanation of the drawing

[0028] FIG. 1 is a drawing showing the image radar unit of an observation device according to an embodiment of the present invention with the reflection unit unfolded. FIG. 2 is a drawing showing the image radar part of an observation device according to an embodiment of the present invention with the reflection part folded. FIG. 3 is a drawing showing the feeder section and the electro-optical / infrared section of an observation device aligned according to an embodiment of the present invention. FIG. 4 is a drawing showing an enlarged view of the electro-optical / infrared section of an observation device according to an embodiment of the present invention. FIGS. 5 and 6 are drawings showing an observation device according to variations of an embodiment of the present invention. FIG. 7 is a flowchart illustrating an observation method according to an embodiment of the present invention. Specific details for implementing the invention

[0029] Hereinafter, embodiments of the present invention will be described in detail with reference to the attached drawings. However, the present invention is not limited to the embodiments disclosed below and may be implemented in various different forms. The embodiments of the present invention are provided merely to ensure that the disclosure of the present invention is complete and to fully inform those skilled in the art of the scope of the invention. To illustrate the embodiments of the present invention, the drawings may be exaggerated, and like reference numerals in the drawings refer to like elements.

[0030] The present invention relates to a multi-sensor integrated observation device and observation method for a satellite payload. Below, an embodiment is described by exemplifying the case where the observation device is mounted on a small satellite. Of course, the details described below may be applied similarly or identically even when the observation device is mounted on various carriers other than small satellites.

[0031] Meanwhile, the multi-sensor integrated observation device and observation method for a satellite payload according to an embodiment of the present invention may also be referred to as a small hybrid payload for space and a method of operating the same. Additionally, the small hybrid payload for space may be referred to as an imaging radar / electro-optical / infrared integrated hybrid payload.

[0032] First, before describing the embodiments of the present invention, a small satellite will be described.

[0033] Artificial satellites (hereinafter referred to as satellites) may include military satellites. Of course, satellites can be diverse, such as weather satellites, communication satellites, and scientific satellites. These satellites can be classified into microsatellites, small satellites, medium satellites, and large satellites based on their weight. Microsatellites may weigh 100 kg or less. Small satellites may weigh more than 100 kg and less than or equal to 500 kg. Medium satellites may weigh more than 500 kg and less than or equal to 1000 kg. Large satellites may weigh more than 1000 kg. Of course, in addition to weight, there may be various criteria for classifying satellites.

[0034] Hereinafter, an example is provided of an observation device according to an embodiment of the present invention being mounted on the satellite body of a small satellite having a weight of more than 100 kg and less than or equal to 500 kg. Of course, the observation device can be mounted on satellites of various weights, such as microsatellites and large satellites.

[0035] At this time, in describing the observation device below, receiving light / heat means that an electro-optical (EO) sensor and an infrared (IR) sensor receive light (visible light) and heat (infrared) through a single tube (hereinafter referred to as the tube (31)). At this time, the electro-optical (EO) sensor and the infrared (IR) sensor are integrated in physical form and are named the electro-optical (EO) / infrared (IR) sensor. Additionally, the optical part having the electro-optical (EO) / infrared (IR) sensor is named the electro-optical / infrared part.

[0036] Meanwhile, although Synthetic Aperture Radar (SAR) sensors are physically distinct from Electro-Optical (EO) and Infrared (IR) sensors, since all sensors (i.e., SAR sensors and Electro-Optical (EO) and Infrared (IR) sensors) are mounted on a single satellite, a payload equipped with both SAR and Electro-Optical (EO) and Infrared (IR) sensors is designated as a SAR / EO / Infrared integrated hybrid payload.

[0038] Hereinafter, an observation device according to an embodiment of the present invention will be described.

[0039] FIG. 1 is a side view exemplarily showing the image radar unit of an observation device according to an embodiment of the present invention with the reflector unit unfolded, and FIG. 2 is a plan view exemplarily showing the image radar unit of an observation device according to an embodiment of the present invention with the reflector unit folded. In addition, FIG. 3 is a perspective view exemplarily showing the feeder unit and the electro-optical / infrared unit of an observation device according to an embodiment of the present invention aligned, and FIG. 4 is a perspective view exemplarily showing an enlarged view of the electro-optical / infrared unit of an observation device according to an embodiment of the present invention.

[0040] Referring to FIGS. 1 to 4, an observation device according to an embodiment of the present invention is capable of being mounted on a satellite and includes a payload (10) that can be mounted on a satellite body, an imaging radar unit (20) that can transmit and receive radio waves and is installed on the payload (10), and an electro-optical / infrared unit (30) that can receive light / heat and is installed on the payload (10) in the same direction as the imaging radar unit (20) transmits and receives radio waves. Of course, the observation device is not limited thereto and may include various additional configurations in addition to the above configurations as long as they ensure survivability and mission performance capabilities in a space environment.

[0041] This observation device can perform multiple different satellite missions, such as not only its original role of collecting various signal information from the Earth's surface, but also the role of photographing the Earth's surface through the imaging radar unit (20) and the role of detecting and tracking targets through the electro-optical / infrared unit (30).

[0042] The mounting section (10) serves to support the imaging radar section (20) and the electro-optical / infrared section (30). Accordingly, the mounting section (10) may be provided in any configuration that can support the imaging radar section (20) and the electro-optical / infrared section (30).

[0043] The payload (10) can be mounted on the satellite body. At this time, the structure in which the payload (10) is mounted on the satellite body can be varied, and since there is no need to specifically limit it, a description thereof is omitted.

[0044] The imaging radar unit (20) is intended to transmit and receive radio waves to photograph the surface of the Earth. The imaging radar unit (20) may be arranged in one direction. The one direction may be a direction perpendicular to one surface of the mounting unit (10).

[0045] The imaging radar unit (20) may include a hub unit, a feeder unit (21) supported by the hub unit and on which an electro-optical / infrared unit (30) can be aligned or overlapped, a reflector unit (22) arranged along the periphery of the feeder unit (21) for reflecting radio waves, and a deployment unit (23) for deploying the reflector unit (22) around the feeder unit (21). Of course, the imaging radar unit (20) may include various additional configurations. For example, the imaging radar unit (20) may further include an RF amplifier connected to the feeder of the feeder unit (21), a transceiver module, a baseband unit, and a data processing unit. In this case, the RF amplifier may include a semiconductor (GaN) power amplifier (SSPA) or a traveling wave tube amplifier (TWTA). The baseband unit performs the role of generating and processing signals, and the data processing unit performs the role of processing and storing the received signals. Meanwhile, the semiconductor power amplifier, traveling wave tube amplifier, transmit / receive module, baseband section, and data processing section are widely known components in the field of satellite imaging radar, so a description thereof is omitted.

[0046] The hub section serves as the center point for the development of the reflection section (22). The hub section may be a member having a circumference. For example, the hub section may be a member with a closed curve shape, and among them, a ring-shaped member. Of course, the hub section may be a member with a plate shape, and among them, a disc-shaped member. A development section (23) may be installed at the edge of the hub section, the reflection section (22) may be connected to the development section (23), and a feeder section (21) may be placed inside the development section (23).

[0047] The feeder unit (21) can transmit and receive radio waves. More specifically, the feeder unit (21) transmits radio waves to the reflection unit (22) in an unfolded state and receives radio waves reflected from the reflection unit (22) in an unfolded state. The feeder unit (21) may include a support member (21a) extending in one direction from one side of the mounting unit (10), a feeder (21b) disposed at the end of the support member (21a), and a connecting member (21c) that supports the feeder (21b) on the support member (21a).

[0048] The support member (21a) may be extended in one direction. There may be multiple support members (21a). For example, there may be three support members (21a). Of course, the number of support members (21a) may vary. Meanwhile, the support member (21a) is intended to position the feeder (21b) at the focal position of the reflector (22), and as long as the support member (21a) satisfies this role, the number, the coupling structure, and the external shape resulting from the coupling structure may vary. One end of the support member (21a) may be supported by the hub. Additionally, the feeder (21b) and the connecting member (21c) may be supported by the other end of the support member (21a).

[0049] The feeder (21b) can receive an RF signal and transmit radio waves to the reflector (22), and can receive radio waves reflected from the reflector (22). The feeder (21b) may include a horn antenna. The feeder (21b) may be connected to the lower part of the connecting member (21c) and may extend downward.

[0050] The number of connecting members (21c) may be the same as that of the supporting members (21a). The connecting members (21c) may extend in the other direction which is a direction intersecting one direction, may be radially connected to the feeder (21b), and may be supported by the supporting members (21a).

[0051] The reflector (22) can reflect radio waves transmitted from the feeder (21b) to the surface of the Earth and reflect radio waves reflected from the surface of the Earth back to the feeder (21b). The reflector (22) may include a mesh form or a carbon fiber reinforced composite (CFRP) material. The reflector (22) may be in a folded state to reduce volume during satellite launch. Additionally, the reflector (22) may be in an unfolded state to reflect radio waves after the satellite enters orbit. The reflector (22) may include a mesh-type reflector (22a) and a plurality of ribs (22b). The mesh-type reflector (22a) may include a molybdenum material and may have a metal, such as gold, plated on its surface. The rib (22b) can be supported by the unfolding section (23), and by the unfolding section (23), it can be erected at a predetermined angle of vertical or near-vertical with respect to one side of the mounting section (10) and can wrap the outer side of the feeder section (21) in a cylinder or a predetermined shape near a cylinder, and can be unfolded radially around the feeder section (21) by the unfolding section (23). By doing so, the mesh-type reflective member (22a) can be folded or unfolded. The rib (22b) may include a carbon fiber reinforced composite material.

[0052] The unfolding section (23) is for unfolding the reflecting section (22) and may have the same number as the ribs (22b). Multiple unfolding sections (23) may be arranged along the circumference of the hub section from the edge side of the hub section. Each of the multiple unfolding sections (23) may include a spring, a pin bracket, a pin, a cable, and a motor. Of course, the unfolding section (23) may also include various connecting parts. A pin bracket may be placed on the edge side of the hub section. The pin may rotatably connect the rib (22b) to the pin bracket. The motor may rotate the rib (22b) around the pin, and this rotation may cause the reflecting section (22) to stand upright and unfold. The cable serves to support each part of the rib (22b) when the rib (22b) rotates due to the operation of the motor.

[0053] Meanwhile, a plurality of unfolding parts (23) may unfold the rib (22b) using their own elastic force. In this case, each of the plurality of unfolding parts (23) may include at least a portion of a shape memory alloy material. For example, each of the plurality of unfolding parts (23) may include a bracket positioned on the edge side of the hub part, a hinge extending in a direction away from the feeder part (21) and having one end mounted on the bracket and having a shape memory alloy material so as to be elastically bent and unfolded, and a socket mounted on the other end of the hinge and supporting the rib (22b). At this time, at least one of the bracket and the socket may include the same material as the hinge.

[0054] The electro-optical / infrared section (30) is intended to receive light / heat (e.g., visible light / infrared) from the Earth's surface to detect and track targets on the ground and in the ocean. The center of the electro-optical / infrared section (30) may be aligned in one direction with the center of the imaging radar section (20). For example, the electro-optical / infrared section (30) may be positioned to be aligned in one direction with the feeder (21b) and the connecting member (21c). Accordingly, optical shielding by the feeder (21b) and the connecting member (21c) can be prevented or minimized.

[0055] The electro-optical / infrared section (30) may also be named the visible light / infrared section (30).

[0056] The electro-optical / infrared section (30) comprises: a tube (31) which is extended in one direction and has an interior that is open in one direction so that light / heat can be incident, and is positioned on one side of the mounting section (10); a main reflector (32) having a hole in its center, which is installed facing the direction in which light / heat is incident on the other end of the tube (31), between one end of the tube (31) close to the end of the support member (21a) and the other end of the tube (31) far from the end of the support member (21a); ​​a sub-reflector (33) which is positioned to face the main reflector (32) on the side of one end of the tube (31) and is aligned in one direction with the main reflector (32); a radial support member (34) which extends radially from one end of the tube (31) toward the sub-reflector (33) to support the sub-reflector (33) on the tube (31); and a main reflector (33) which is positioned on the other end surface of the tube (31). It may include a signal processor (35) that receives incident light / heat reflected by the reflector (32) and auxiliary reflector (33) and processes the image. At this time, the electro-optical / infrared section (30) is aligned in one direction with the feeder (21b) and the connecting member (21c), and the radial support member (34) may be aligned in one direction with the connecting member (21c) and overlapped in the other direction to minimize light / heat shielding, and may be radially aligned with the support member (21a). Accordingly, when the image radar section (20) deploys the reflector (22), the front opening (incident opening) of the electro-optical / infrared section (30) may be exposed toward the surface of the earth in the same direction as the direction in which the image radar section (20) transmits and receives radio waves, and light / heat may be received therefrom.

[0057] Although an observation device according to an embodiment of the present invention has been described above with reference to FIGS. 1 to 4, the observation device may be implemented in various forms, including the following variations. In this case, the differences between the embodiment and the variations are described below, and descriptions of redundant content are omitted or briefly explained.

[0058] FIGS. 5 and 6 are drawings showing an observation device according to the first and second variations of an embodiment of the present invention.

[0059] Referring to FIG. 5, the feeder section (21) of the observation device includes a support member (21a) extending in one direction from one side of the mounting section (10), a feeder (21b) positioned at the end of the support member (21a), and a connecting member (21c) that supports the feeder (21b) on the support member (21a). At this time, the electro-optical / infrared section (30) may be positioned to be separated from the feeder (21b) and the connecting member (21c) in the other direction, which is a direction intersecting with the one direction. Accordingly, the electro-optical / infrared section (30) can receive light / heat from the Earth's surface from the outside of the feeder (21b) and the connecting member (21c).

[0060] Referring to FIG. 6, the feeder section (21) of the observation device comprises a support member (21a) extending in one direction from one side of the mounting section (10), a sub-reflector member (21d) disposed at the end of the support member (21a) and supported by the support member (21a), a feeder (21b) spaced apart from the sub-reflector member (21d) toward one side of the mounting section (10), and a connecting member (21c) that supports the feeder (21b) on the support member (21a) or the sub-reflector member (21d). At this time, the electro-optical / infrared section (30) may be disposed to move away from the sub-reflector member (21d) in the other direction which is a direction intersecting with the one direction.

[0061] In such variations, the arrangement of the feeder (21b) may differ, a sub-reflective member (21d) may be added, and the electro-optical / infrared section (30) may be spaced apart from the center of the imaging radar section (20) in the other direction, which is a direction intersecting one direction, by the size of the opening of the electro-optical / infrared section (30).

[0063] FIG. 7 is a flowchart illustrating an observation method according to an embodiment of the present invention.

[0064] Hereinafter, an observation method according to an embodiment of the present invention will be described. The observation method according to an embodiment of the present invention may be a method utilizing the aforementioned observation method, and since the aforementioned details regarding the observation method may be applied as is, the description of redundant details will be omitted.

[0065] An observation method according to an embodiment of the present invention comprises the steps of: launching a satellite body equipped with an imaging radar unit (20) capable of transmitting and receiving radio waves and an electro-optical / infrared unit (30) capable of receiving light / heat into space and positioning it in orbit (S110); transmitting and receiving radio waves through the imaging radar unit (20) (S120); receiving light / heat through the electro-optical / infrared unit (30) (S130); and generating information about an observation area (also referred to as a surveillance area) using at least one of the transmitted and received radio waves and the received light / heat (S140).

[0066] Here, the process of transmitting and receiving radio waves through the imaging radar unit (20) (S120) and the process of receiving light / heat through the electro-optical / infrared unit (30) (S130) may proceed sequentially according to an arbitrarily determined order. That is, the process of transmitting and receiving radio waves through the imaging radar unit (20) (S120) may be performed first, or the process of receiving light / heat through the electro-optical / infrared unit (30) (S130) may be performed first. Additionally, the process of transmitting and receiving radio waves through the imaging radar unit (20) (S120) and the process of receiving light / heat through the electro-optical / infrared unit (30) (S130) may be performed selectively as only one of the processes, or simultaneously, depending on the environmental conditions of the observation area, such as weather conditions or day and night. That is, the process of transmitting and receiving radio waves through the image radar unit (20) (S120) and the process of receiving light / heat through the electro-optical / infrared unit (30) (S130) are independent elements that can be continuously performed for information generation, and they may not correspond to a time-series relationship where one process is performed after the other process is completed, and it is also obvious that there may not be a sequential relationship between them.

[0067] This observation method may use only transmitted and received radio waves, only received light / heat, or a combination of transmitted and received radio waves and received light / heat, depending on the time elapsed and weather conditions of the monitoring area.

[0068] First, a satellite body equipped with an imaging radar unit (20) and an electro-optical / infrared unit (30) is launched into space and placed in orbit (S110). That is, an observation device is mounted on the satellite. Then, the satellite is launched toward orbit using a launch vehicle. Afterward, at an appropriate time, the satellite is separated from the launch vehicle and placed into orbit.

[0069] In addition, the reflector (22) of the image radar unit (20), which can reflect radio waves and be folded and unfolded, is deployed (S111).

[0070] Radio waves are transmitted and received through the imaging radar unit (20) (S120). To do this, radio waves are transmitted and received through the feeder unit (21) of the imaging radar unit (20) located at the center of the reflection unit (22). That is, radio waves are transmitted and received by supplying an RF signal to the feeder (21b).

[0071] Light / heat is received through the electro-optical / infrared section (30) (S130). In the preceding process, as the reflector (22) is unfolded, the opening of the electro-optical / infrared section (30) located within the reflector (22) can be exposed toward the surface of the earth, and light / heat can be received smoothly therefrom. For example, light / heat can be incident on the body (31) of the electro-optical / infrared section (30) whose center is aligned with the feeder section (21), and the light / heat can be reflected in sequence by the main reflector (32) and the sub-reflector (33) of the electro-optical / infrared section (30) placed within the body (31), and the light / heat incident by reflecting the main reflector (32) and the sub-reflector (33) can be received by the signal processor (35) for image processing. At this time, the shielding of light / heat incident on the main mirror (32) can be minimized by utilizing the alignment state between the radial connecting member (34) supported by the auxiliary mirror (33), for example, the spider and the feeder part (21).

[0072] Alternatively, light / heat can be incident on the body (31) of the electro-optical / infrared section (30) which is spaced from the center of the feeder section (21) by the size of the opening of the electro-optical / infrared section (30), and the light / heat can be reflected in sequence by the main reflector (32) and the sub-reflector (33) of the electro-optical / infrared section (30) disposed within the body (31), and the light / heat incident by reflecting the main reflector (32) and the sub-reflector (33) can be received by the signal processor (35) for image processing.

[0073] Accordingly, information about an observation area can be generated using at least one of the transmitted and received radio waves and the received light / heat (S140). That is, a first information can be generated by signal processing the radio waves, a second information can be generated by image processing the light / heat, a merged information can be generated by merging the first information and the second information, and the merged information can be output as observation information.

[0075] As such, in an embodiment of the present invention, optical / infrared images and radar images can be obtained simultaneously or individually by combining the electro-optical / infrared unit (30) and the imaging radar unit (20) into a single, compact payload. More specifically, by simultaneously capturing images of the same observation area using the electro-optical / infrared unit (30) and the imaging radar unit (20), heterogeneous information can be obtained simultaneously, thereby improving timeliness compared to the existing satellite operation concept.

[0076] In addition, by acquiring multiple types of information (i.e., heterogeneous information) in this way, complex missions can be performed, thereby improving the cost-effectiveness, efficiency, and timeliness of satellite operations.

[0077] In addition, by the electro-optical / infrared unit (30) receiving light / heat and processing images, the electro-optical / infrared unit (30) can supplement the visual judgment lacking in the imaging radar unit (20), thereby improving the quality of information. Furthermore, by the electro-optical / infrared unit (30) and the imaging radar unit (20) exchanging mutually lacking information, it is possible to reinforce information using only a single platform.

[0079] The above embodiments of the present invention are for the purpose of illustrating the present invention and are not intended to limit the present invention. It should be noted that the configurations and methods disclosed in the above embodiments of the present invention may be combined or intersected in various forms and modified, and that such modified examples may also be considered within the scope of the present invention. That is, the present invention will be implemented in various different forms within the scope of the claims and equivalent technical concepts, and those skilled in the art to which the present invention pertains will understand that various embodiments are possible within the scope of the technical concept of the present invention. Explanation of the symbols

[0080] 10: Mounting section 20: Video Radar Department 30: Electro-optical / Infrared Section

Claims

Claim 1 An observation device capable of being mounted on a satellite, comprising: a payload capable of being mounted on a satellite body; an imaging radar unit capable of transmitting and receiving radio waves, installed on the payload, and having an imaging radar (SAR) sensor; an electro-optical / infrared unit capable of receiving light / heat, installed on the payload in the same direction as the imaging radar unit transmits and receives radio waves, and having an electro-optical (EO) / infrared (IR) sensor physically separated from the imaging radar (SAR) sensor; wherein the center of the electro-optical / infrared unit is aligned in one direction with the center of the imaging radar unit, or is spaced from the center of the imaging radar unit in the other direction by the aperture size of the electro-optical / infrared unit in a direction intersecting the one direction, so as to minimize shielding by the imaging radar unit. Claim 2 delete Claim 3 An observation device according to claim 1, wherein the imaging radar unit comprises: a feeder unit to which the electro-optical / infrared unit may be aligned or overlapped; a reflector unit disposed along the periphery of the feeder unit for reflecting radio waves; and a deployment unit for deploying the reflector unit around the feeder unit. Claim 4 In claim 3, the reflector comprises a mesh form or a carbon fiber reinforced composite (CFRP) material, and the unfolding portion comprises at least a part of a material that can be elastically bent and unfolded, or an observation device comprising a cable and a motor. Claim 5 The feeder portion of claim 3 comprises: a support member extending in one direction from one side of the mounting portion; a feeder disposed at the end of the support member; and a connecting member supporting the feeder on the support member; and the electro-optical / infrared portion is an observation device arranged to be aligned in one direction with the feeder and the connecting member, or to be disposed away from the feeder and the connecting member in another direction that is a direction intersecting with the one direction. Claim 6 The feeder portion of claim 3 comprises: a support member extending in one direction from one side of the mounting portion; a sub-reflector member disposed at the end of the support member and supported by the support member; a feeder spaced apart from the sub-reflector member toward one side of the mounting portion; and a connecting member supporting the feeder on the support member or the sub-reflector member; and the electro-optical / infrared portion is an observation device disposed to move away from the sub-reflector member in another direction that is a direction intersecting the one direction. Claim 7 The observation device according to claim 5 or claim 6, wherein the feeder comprises a horn antenna. Claim 8 In claim 3, the feeder part comprises: a support member extending in one direction from one side of the mounting part; a sub-reflector member disposed at the end of the support member and supported by the support member; and a feeder disposed on one side of the mounting part spaced apart from the end of the support member and facing the sub-reflector member in the one direction; and the electro-optical / infrared part is an observation device disposed to move away from the sub-reflector member and the feeder in another direction that is a direction intersecting the one direction. Claim 9 An observation device according to claim 5, claim 6, or claim 8, wherein the imaging radar unit further comprises an RF amplifier connected to the feeder. Claim 10 In claim 9, the RF amplifier is an observation device comprising a semiconductor (GaN) power amplifier (SSPA) or a traveling wave tube amplifier (TWTA). Claim 11 An observation device according to claim 5, wherein the electro-optical / infrared part comprises: a tube extending in the one direction and having an interior open in the one direction so as to allow light / heat to be incident thereon, and disposed on one side of the mounting part; a main reflector having a hole in the center, installed facing the direction in which light / heat is incident on the other end of the tube, between one end of the tube close to the end of the support member and the other end of the tube far from the end of the support member; a sub-reflector disposed on the one end of the tube to face the main reflector and aligned with the main reflector in the one direction; and a radial support member extending radially from one end of the tube toward the sub-reflector to support the sub-reflector on the tube. Claim 12 An observation device according to claim 11, wherein the electro-optical / infrared part is aligned in one direction to the feeder and the connecting member, and the radial support member is aligned in one direction to the connecting member and overlapped in the other direction and radially aligned to the support member to minimize shielding. Claim 13 An observation method comprising: a process of launching a satellite body equipped with an imaging radar unit capable of transmitting and receiving radio waves and an electro-optical / infrared unit capable of receiving light / heat into space and positioning it in orbit; a process of transmitting and receiving radio waves through the imaging radar unit; a process of receiving light / heat through the electro-optical / infrared unit; and a process of generating information about an observation area using at least one of the transmitted and received radio waves and the received light / heat; wherein the process of receiving light / heat through the electro-optical / infrared unit further comprises a process of minimizing shielding of light / heat using the alignment state of the electro-optical / infrared unit and the imaging radar unit. Claim 14 An observation method according to claim 13, wherein only transmitted and received radio waves, only received light / heat, or a combination of transmitted and received radio waves and received light / heat are used depending on the time elapsed and weather conditions of the observation area. Claim 15 An observation method according to claim 13, wherein the process of generating information about the observation area further comprises: a process of signal processing the radio waves to generate first information; a process of image processing the light / heat to generate second information; and a process of merging the first information and the second information to generate merged information and outputting the merged information as observation information. Claim 16 An observation method according to claim 13, comprising, between the process of launching the satellite body into space and positioning it in orbit and the process of transmitting and receiving radio waves through the imaging radar unit, the process of deploying the reflector of the imaging radar unit, which is capable of reflecting radio waves and can be folded and unfolded; and the process of transmitting and receiving radio waves through the imaging radar unit comprises the process of transmitting and receiving radio waves through the feeder of the imaging radar unit located at the center of the reflector. Claim 17 An observation method according to claim 16, wherein the process of minimizing shielding of light / heat using the alignment state of the electro-optical / infrared section and the imaging radar section comprises: a process of injecting light / heat into the body of the electro-optical / infrared section, the center of which is aligned with the feeder section; a process of reflecting light / heat in the order of the main reflector and the sub-reflector of the electro-optical / infrared section disposed within the body; and a process of minimizing shielding of light / heat incident on the main reflector using the alignment state between the radial connecting member supporting the sub-reflector and the feeder section. Claim 18 An observation method according to claim 16, wherein the process of receiving light / heat through the electro-optical / infrared section comprises: the process of injecting light / heat into the body of the electro-optical / infrared section spaced apart from the feeder section by the aperture size of the electro-optical / infrared section; and the process of reflecting light / heat in the order of the main reflector and the sub-reflector of the electro-optical / infrared section disposed within the body. Claim 19 An observation method according to any one of claims 13 to 18, wherein the satellite comprises a small satellite.

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