Abstract: A spacecraft includes: a main-reflection unit configured to reflect and emit a radio wave outside, a sub-reflection unit configured to face the main-reflection unit, a radiator arranged to face the sub-reflection unit and configured to radiate the radio wave in a direction of the sub-reflection unit, a main body configured to be able to accommodate at least one part of the sub-reflection unit therein, and a delivery device connected to the sub-reflection unit and configured to deliver the sub-reflection unit, at least one part of which is accommodated in the main body, to a position where the sub-reflection unit is able to reflect the radio wave radiated from the radiator to the main-reflection unit and cause the main-reflection unit to radiate the radio wave outside.

Abstract: Spacecraft and antenna apparatus that can be more easily deployed from a stored state can include: a main-reflection unit including a plurality of ribs formed to be deployable in a stored state in which the ribs are folded and a sheet body provided between a plurality of the ribs and configured to be capable of reflecting a radio wave radiated from a radiator and emitting the radio wave outside, and a restriction member configured to restrict deployment of the plurality of ribs in the stored state, and release the restriction by operation of a restriction release member different from the main-reflection unit.

Abstract: Provided are a spacecraft control system, a spacecraft control method, and a server device capable of quickly transmitting control data to a spacecraft. The spacecraft system includes: a plurality of spacecrafts; a plurality of small communicators that transmit control data related to imaging operations of the spacecrafts to the spacecrafts; and at least one ground station that receives, from the spacecrafts, captured image data related to images captured by the spacecrafts and space position data for the spacecrafts, and transmits identification data for the small communicators to the spacecrafts, in which each of the spacecrafts includes at least a first reception device that receives the control data transmitted from the small communicators, a control device that controls an imaging operation of the spacecraft on the basis of the control data received by the first reception device, and an imaging device that executes the imaging operation.

Abstract: To provide a connection adapter and a horn antenna measurement device capable of measuring the performance of a system of a horn antenna on the ground without removing the horn antenna mounted on a spacecraft even immediately before the launch, while suppressing radio wave leakage to an external space. A connection adapter (200) includes a first waveguide (201) that is provided inside the connection adapter and connected to a waveguide portion (260) connected to a horn antenna (100), in which the connection adaptor is detachably fitted into the horn antenna, is connected to a measurement instrument (300) via a second waveguide (250) coupled to the first waveguide, and guides radio waves radiated from the horn antenna to the measurement instrument in a closed system.

Abstract: [Problem] To provide a spacecraft having a more effective arrangement of amplifiers. [Solution] Provided is a spacecraft comprising: a main body having a housing space for housing an electronic device within; an oscillator configured to output a radio wave including a frequency in a predetermined frequency band; an amplifier disposed on an exterior of the main body so as to be exposed to space and configured to amplify the power of the radio wave output by the oscillator; and an antenna, disposed on the exterior of the main body, for emitting the radio wave to the outside at the power amplified by the amplifier.

Abstract: Deployable reflectors and antennas and spacecraft using such reflectors are disclosed. An example disclosed reflector includes: a hub having a cross-section formed in a circular, elliptical or polygonal shape; a plurality of ribs, each rib having an inner side surface facing an outer peripheral side of the hub when folded, and an outer side surface that is a surface opposite to the inner side surface, the plurality of ribs being folded to be wound around an outer periphery of the hub such that the inner side surface of each rib and the outer side surface of its adjacent rib partially face each other or the outer side surface of each rib and the inner side surface of its adjacent rib partially face each other, each rib being deployed in a parabolic shape; and a sheet installed across each of the plurality of ribs and capable of reflecting radio waves.

Abstract: Antenna apparatus and spacecraft to be deployed in a more compactly stored state are disclosed. In an example of the disclosed technology, a spacecraft includes: a main-reflection unit configured to reflect and emit a radio wave outside, a sub-reflection unit configured to face the main-reflection unit, a radiator arranged to face the sub-reflection unit and configured to radiate the radio wave in a direction of the sub-reflection unit, a main body configured to be able to accommodate at least one part of the sub-reflection unit therein, and a delivery device connected to the sub-reflection unit and configured to deliver the sub-reflection unit, at least one part of which is accommodated in the main body, to a position where the sub-reflection unit is able to reflect the radio wave radiated from the radiator to the main-reflection unit and cause the main-reflection unit to radiate the radio wave outside.

Abstract: Antenna apparatus and spacecraft to be deployed in a more easily stored state are disclosed. In an example of the disclosed technology, and antenna apparatus includes: a main-reflection unit including a plurality of ribs formed to be deployable in a stored state in which the ribs are folded and a sheet body provided between a plurality of the ribs and configured to be capable of reflecting a radio wave radiated from a radiator and emitting the radio wave outside, and a restriction member configured to restrict deployment of the plurality of ribs in the stored state, and release the restriction by operation of a restriction release member different from the main-reflection unit.

Abstract: An expandable antenna includes: a plurality of ribs arranged with a regulated angular pitch at an outer circumferential portion of a hub; and a metal mesh installed between the plurality of adjacent ribs, wherein each of the plurality of ribs is formed in a horizontally elongated thin flat plate shape with elasticity, and a segment to which the metal mesh is attached is formed in a parabolic shape. A flat plane of each of the plurality of ribs is arranged so as to be substantially parallel to a central axis of the hub. The object of the present invention is to provide the expandable antenna which can be easily expanded in outer space with a simple structure and can realize a desired shape after expansion.

Abstract: Deployable reflectors and antennas and spacecraft using such reflectors are disclosed. An example disclosed reflector includes: a hub having a cross-section formed in a circular, elliptical or polygonal shape; a plurality of ribs, each rib having an inner side surface facing an outer peripheral side of the hub when folded, and an outer side surface that is a surface opposite to the inner side surface, the plurality of ribs being folded to be wound around an outer periphery of the hub such that the inner side surface of each rib and the outer side surface of its adjacent rib partially face each other or the outer side surface of each rib and the inner side surface of its adjacent rib partially face each other, each rib being deployed in a parabolic shape; and a sheet installed across each of the plurality of ribs and capable of reflecting radio waves.

Abstract: An expandable antenna includes: a plurality of ribs arranged with a regulated angular pitch at an outer circumferential portion of a hub; and a metal mesh installed between the plurality of adjacent ribs, wherein each of the plurality of ribs is formed in a horizontally elongated thin flat plate shape with elasticity, and a segment to which the metal mesh is attached is formed in a parabolic shape. A flat plane of each of the plurality of ribs is arranged so as to be substantially parallel to a central axis of the hub. The object of the present invention is to provide the expandable antenna which can be easily expanded in outer space with a simple structure and can realize a desired shape after expansion.

Abstract: The present invention has the object of simplifying apparatus configuration and avoiding a requirement for calibration. The present invention achieves the above object by forming a detection sheet element that retains in a predetermined array pitch a plurality of conductive detection lines that are lead lines formed by etching or the like on a non-conductive thin film that can be exposed in a space environment. A detection circuit connected to each detection line of the detection sheet element is provided. When an object flying in space collides with the detection sheet body, since a detection line on the detection sheet element is ruptured, constant monitoring of the conductivity of the detection line by the detection circuit enables detection of the object flying in space that has collided with the detection sheet element when a detection line is ruptured.

Abstract: The present invention has the object of simplifying apparatus configuration and avoiding a requirement for calibration. The present invention achieves the above object by forming a detection sheet element that retains in a predetermined array pitch a plurality of conductive detection lines that are lead lines formed by etching or the like on a non-conductive thin film that can be exposed in a space environment. A detection circuit connected to each detection line of the detection sheet element is provided. When an object flying in space collides with the detection sheet body, since a detection line on the detection sheet element is ruptured, constant monitoring of the conductivity of the detection line by the detection circuit enables detection of the object flying in space that has collided with the detection sheet element when a detection line is ruptured.