Abstract: A debris removal satellite includes a capture device, a thruster of a chemical propulsion method, and a propellant tank to store chemical fuel. A solar array wing is operable in an orbit at an orbital altitude higher than a congested orbit region congested with satellites forming a satellite constellation. The debris removal satellite is built in advance for future use as a satellite to be launched, and when a debris intrusion alarm to give a warning about intrusion of debris into the congested orbit region is issued, propellant is loaded into the propellant tank and the debris removal satellite is launched by a rocket built in advance for future use as a launch rocket. The debris removal satellite captures capture-target debris at an orbital altitude higher than the congested orbit region, and operates a propulsion device with the capture-target debris being captured.

Abstract: An apparatus communication device (950) communicates with at least one of a parent satellite (310) and a child satellite (320). A control unit (110) generates a control command (51) to capture debris by sandwiching the debris between the parent satellite (310) and the child satellite (320) and carry out an active control operation during orbital descent on a flying object which is the parent satellite (310), the debris, and the child satellite (320) being connected together. Then, the control unit (110) transmits the control command (51) to at least one of the parent satellite (310) and the child satellite (320) via the apparatus communication device (950).

Abstract: A satellite constellation forming system forms a satellite constellation (20) having a plurality of orbital planes (21) in each of which a plurality of satellites fly at the same orbital altitude. A satellite constellation forming unit forms the satellite constellation (20) in which orbital altitudes of the orbital planes (21) are mutually different. Furthermore, in the satellite constellation (20), relative altitude differences between adjacent orbital planes in the plurality of orbital planes are sequentially arranged to be sinusoidal. The satellite constellation forming unit sequentially changes an orbital altitude (23) of each orbital plane of the plurality of orbital planes while maintaining a sinusoidal arrangement of the relative altitude differences between adjacent orbital planes in the plurality of orbital planes.

Abstract: A satellite constellation (200) comprises three artificial satellites (210A to 210C) that monitor a target area of the Earth (101). Each artificial satellite circulates on elliptical orbits having sun-synchronization and an orbit inclination angle. A long axis of each elliptical orbit forms an equal angle with each long axis of two adjacent elliptical orbits in a latitude direction.

Abstract: In a satellite constellation forming system, each satellite in an orbit satellite group includes a propulsion device to change velocity of each satellite in the orbit satellite group. A satellite constellation forming unit causes propulsion devices of satellites in the orbit satellite group to operate in synchronization, for each orbital plane of the plurality of orbital planes. The satellite constellation forming unit causes each satellite in an orbit satellite group in a first orbital plane of the plurality of orbital planes to perform an acceleration and deceleration process of repeating operation of accelerating for a first time period and then decelerating for the first time period. The satellite constellation forming unit causes each satellite in an orbit satellite group in an orbital plane adjacent to the first orbital plane to start the acceleration and deceleration process after a delay of a second time period.

Abstract: A satellite constellation forming system forms a satellite constellation (20) including two orbital planes each having a different normal direction and in each of which the same number of satellites fly. A satellite constellation forming unit gradually changes an orbital altitude of at least one orbital plane of the two orbital planes from a state in which satellite passage timings of satellites flying in the two orbital planes do not coincide with each other at an intersection neighborhood point (Pc) between the two orbital planes in each of the two orbital planes, while maintaining the state in which the satellite passage timings do not coincide with each other.

Abstract: A satellite constellation forming system (100) forms a satellite constellation (20). The satellite constellation (20) is composed of a satellite group (300). In the satellite constellation (20), the satellite group (300) provides a service cooperatively. The satellite constellation (20) has a plurality of orbital planes in which a plurality of satellites (30) fly at the same orbital altitude in each orbital plane (21). A satellite constellation forming unit (110) forms the satellite constellation (20) in which orbital altitudes of the plurality of orbital planes (21) are mutually different.

Abstract: A device that can realize satellite communication with a popularized mobile phone in a case a large number of users communicate at a same time such as in a case where disaster strikes and the like. An external battery for charging a mobile phone includes a satellite antenna for performing satellite communication via a satellite communication channel and a satellite communication unit which causes the mobile phone to perform the satellite communication via the satellite antenna. The mobile phone and the external battery are connected with a cable and the like, and thereby a satellite communication terminal is configured.

Abstract: A device that can realize satellite communication with a popularized mobile phone in a case a large number of users communicate at a same time such as in a case where disaster strikes and the like. An external battery for charging a mobile phone includes a satellite antenna for performing satellite communication via a satellite communication channel and a satellite communication unit which causes the mobile phone to perform the satellite communication via the satellite antenna. The mobile phone and the external battery are connected with a cable and the like, and thereby a satellite communication terminal is configured.

Abstract: A moving object image capture system 100 that captures an image of a moving object includes flying vehicles 1 each of which mounts a camera that captures an image of an earth surface, and captures an image of the earth surface locating a specified coordinate position by the camera; a moving object 9 which receives distance measurement radio waves transmitted from navigation satellites to measure a coordinate position of the moving object 9 and transmits an image capture request signal for requesting image-taking of the earth surface locating the measured coordinate position; and a ground station apparatus 12 which receives the image capture request signal from the moving object, transmits an image capture instruction signal including the coordinate position of the moving object to one of the flying vehicles, causes the camera mounted on the flying vehicle to capture the image of the earth surface locating the coordinate position of the moving object, and receives from the flying vehicle imagery data obtained

Abstract: A light-weight and highly rigid mirror support structure is provided which is capable of maintaining a relation between the relative positions of a main mirror and an auxiliary mirror even with environmental variations in the place of installation or deformations of a mounting surface, and of preventing a deformation of the main mirror and the auxiliary mirror which would otherwise cause performance deterioration. A main mirror (1) and an auxiliary mirror (2) are disposed a predetermined distance apart from each other in a face-to-face relation. A main mirror support member (3) and an auxiliary mirror support member (4) serve to support the main mirror (1) and the auxiliary mirror (2), respectively. A plurality of rods (15a) connect the main mirror support member (4) and the auxiliary mirror support member (4) with each other.

Abstract: A light-weight and highly rigid mirror support structure is provided which is capable of maintaining a relation between the relative positions of a main mirror and an auxiliary mirror even with environmental variations in the place of installation or deformations of a mounting surface, and of preventing a deformation of the main mirror and the auxiliary mirror which would otherwise cause performance deterioration. A main mirror (1) and an auxiliary mirror (2) are disposed a predetermined distance apart from each other in a face-to-face relation. A main mirror support member (3) and an auxiliary mirror support member (4) serve to support the main mirror (1) and the auxiliary mirror (2), respectively. A plurality of rods (15a) connect the main mirror support member (4) and the auxiliary mirror support member (4) with each other.