Abstract: A radio wave generating apparatus includes a controlling section and a radio wave transmitting section. The controlling section includes an OAM radio wave information setting section for generating a transmission radio wave signal according to an OAM mode order, a phase changing section for linearly changing a phase of the transmission radio wave signal over time depending on the OAM mode order, and a complex signal generating section for generating a complex signal from the transmission radio wave signal that has been changed in phase by the phase changing section and a reference signal. The radio wave transmitting section includes a complex signal converting section for breaking down a signal component of the complex signal into a real part and an imaginary part, a wireless processing section for generating a wireless signal from the signal component of the complex signal, and an array antenna.

Abstract: A three-dimensional structure spacecraft having a tensegrity structure appropriately controls a vibration even when the three-dimensional structure spacecraft is subjected to air resistance, solar wind disturbance, or the like, lands a satellite or a planet, and performs work or the like. The three-dimensional structure spacecraft includes a plurality of compression members and a plurality of tension members. Three or more of the tension members are connected to each of ends of the compression members. A three-dimensional structure formed by the compression members and the tension members is maintained by tension of the tension members. A variable damping force damper is disposed in at least either the compression members or the tension members. The variable damping force damper is configured to generate a predetermined force in a longitudinal direction of the compression members or in a longitudinal direction of the tension members.

Abstract: A stereostructure spacecraft of the present invention comprises multiple deployable beam members, multiple tension members, and a spacecraft for storing the deployable beam members and the tension members. The stereostructure spacecraft is formed by deploying the deployable beam members and the tension members around the spacecraft. The deployable beam members stored in the spacecraft are deployed and arranged equidistantly in directions of multiple rotational symmetry axes, the rotational symmetry axes being rotational symmetry axes of a virtual polyhedron that is formed to have a substantial center of the spacecraft as an origin. The tension members support two end portions of two adjacent deployable beam members with tension. The respective end portions of the deployable beam members are simultaneously supported by three or more of the tension members.

Abstract: To provide an electromagnetic wave generation system capable of generating structured electromagnetic waves by leveraging the flexibility of OAM-containing waves to detect changes in wave structure during interactions with objects and enable applications in radar and sensors. The system comprises a computing device and an electromagnetic wave generation device. The computing device includes: an input unit for receiving inputs such as an orthogonal basis pair, geometric structural information (azimuth, elevation, radius, rotation angle); a rotation operation unit to rotate geometric information based on the rotation angle; and a display unit to visualize a sphere with the orthogonal basis pair at the poles and rotated geometric information.

Abstract: Provided is an electromagnetic wave transmitting/receiving device capable of transmitting OAM radio waves in at least two directions and receiving OAM radio waves arriving from at least two directions. This electromagnetic wave transmitting/receiving device includes: a plurality of antennas; a plurality of phase shifters each connected to a corresponding one of the antennas; a phase shift controller that controls phase-shifting by the phase shifters; and an antenna selector that selects an antenna to be used for transmitting or receiving electromagnetic waves from among the plurality of antennas. The antenna selector selects three or more antennas oriented in at least two different directions from among the plurality of antennas in accordance with directions in which the electromagnetic waves are transmitted or received.

Abstract: A radio wave analysis apparatus analyzes a radio wave having a geometric structure, and includes: a radio signal acquisition section that acquires, as a reception radio signal, a complex signal of a reception electric field of each of elements of an array antenna; an orthogonal basis expansion section that calculates orthogonal basis components including an orbital angular momentum component from the reception radio signal; a reference structure acquisition section that acquires reference structure information for identifying components of the radio wave corresponding to first and second orthogonal bases, respectively, used in modulation of the radio wave through a geometric structure; and a reconstruction computation section that uses the orthogonal basis components and the reference structure information to compute, as a reconstructed geometric structure, an elevation angle, an azimuth angle, and a radius on a spherical surface having the first and second orthogonal bases as poles.

Abstract: An electromagnetic wave information processing device includes an input unit configured to receive a measurement result that measures electromagnetic waves incident on a spacecraft from substantially an omnidirection. A calculation is performed based on information received by the input unit; and an output unit is configured to output a calculation result. The calculation is based on the measurement result received by the input unit, a local omnidirectional feature which is a coefficient of a local basis function indicating a distribution of the electromagnetic waves received by the input unit in a spacecraft coordinate system centered on the spacecraft at a predetermined position in an outer space, and an entire omnidirectional feature which is a coefficient of an entire basis function based on local omnidirectional features and the predetermined positions, thereby generating a map indicating a distribution of an entire electromagnetic wave source including a ground surface and the outer space.

Abstract: A spacecraft includes: an antenna unit 20 including a first layer film 11 and a second layer film 14, the first layer film 11 including a plurality of slit-like openings 13 in a film that does not allow transmission of an electromagnetic wave 16, and the second layer film 14 including a light receiving element 15 that detects a coherent electromagnetic wave transmitting through the plurality of openings; and a processing unit 21 configured to estimate an arrival direction of the electromagnetic wave from signal intensities of the electromagnetic waves detected by the light receiving element.

Abstract: A three-dimensional structure spacecraft having a tensegrity structure appropriately controls a vibration even when the three-dimensional structure spacecraft is subjected to air resistance, solar wind disturbance, or the like, lands a satellite or a planet, and performs work or the like. The three-dimensional structure spacecraft includes a plurality of compression members and a plurality of tension members. Three or more of the tension members are connected to each of ends of the compression members. A three-dimensional structure formed by the compression members and the tension members is maintained by tension of the tension members. A variable damping force damper is disposed in at least either the compression members or the tension members. The variable damping force damper is configured to generate a predetermined force in a longitudinal direction of the compression members or in a longitudinal direction of the tension members.

Abstract: An artificial satellite and artificial satellite system has power transmission and reception efficiency and includes an expandable solar panel that generates power, expandable power transmitting antennas, and expandable beam members to connect the solar panel and the power transmitting antennas to each other. The beam members are expanded from being provided in the artificial satellite, on a plurality of rotational symmetry axes of an imaginary polyhedron formed with substantially a center of the artificial satellite as an origin. The beam members are arranged at substantially equal distances in directions of the rotational symmetry axes. A light receiving surface of the solar panel and installation surfaces of the power transmitting antennas, when expanded, are substantially perpendicular to a solar panel rotational symmetry axis passing through a center of the solar panel, and being arranged on opposite sides of a plane passing through the center of the artificial satellite.

Abstract: An environment evaluation system stores first data on an ecosystem of a conservation target area, second data on land use of the conservation target area, and third data on a conservation scenario in the conservation target area. The environment evaluation system extracts a network structure where areas having natural capital in the conservation target area are nodes based on the second data, estimates an ecosystem function network representing types of ecosystem functions of the nodes and time-related functions of interactions between the nodes based on the first data, the third data, and the network structure, calculates an economic value of a change in the ecosystem function of the node using a conservation scenario for the node based on a budget constraint related to the conservation scenario for the node which is calculated from the ecosystem function network and the third data, and outputs the economic value.

Abstract: The space structure control system includes: a space structure; an artificial satellite connected to the space structure; and a propulsion device installed on the artificial satellite and configured to control an orbit and an attitude of the artificial satellite, in which the space structure includes a film-like structure, a solar reflectance control device that controls a spatial pattern of a solar reflectance in a reflecting mirror provided in the film-like structure, and a shape retaining device that is connected to the film-like structure, the propulsion device rotates the film-like structure to generate a centrifugal force, the solar reflectance control device controls a solar reflectance in the reflecting mirror to control a solar radiation pressure to be applied to the reflecting mirror, a three-dimensional shape of the film-like structure is controlled based on the centrifugal force generated by the rotation of the film-like structure and the solar radiation pressure, and the shape of the film-like st

Abstract: An artificial satellite and artificial satellite system has power transmission and reception efficiency and includes an expandable solar panel that generates power, expandable power transmitting antennas, and expandable beam members to connect the solar panel and the power transmitting antennas to each other. The beam members are expanded from being provided in the artificial satellite, on a plurality of rotational symmetry axes of an imaginary polyhedron formed with substantially a center of the artificial satellite as an origin. The beam members are arranged at substantially equal distances in directions of the rotational symmetry axes.

Abstract: An electromagnetic wave processing system mounted on a spacecraft including a plurality of antennas includes: a measurement apparatus configured to process measurement signals of electromagnetic waves acquired by the plurality of antennas; an attitude detection apparatus configured to detect an attitude of the spacecraft; a rotation control apparatus configured to control rotation of the spacecraft; and a calculation apparatus. The rotation control apparatus rotates the spacecraft about a center of gravity around a plurality of rotational axes with respect to an inertial space. The measurement apparatus performs measurement at a plurality of attitudes changed by the rotation. The calculation apparatus calculates an intensity distribution of electromagnetic waves acquired by the plurality of antennas using an interference waveform obtained by multiplying measurement signals obtained from different antennas in the measurement signals obtained at the plurality of attitudes.

Abstract: A stereostructure spacecraft of the present invention comprises multiple deployable beam members, multiple tension members, and a spacecraft for storing the deployable beam members and the tension members. The stereostructure spacecraft is formed by deploying the deployable beam members and the tension members around the spacecraft. The deployable beam members stored in the spacecraft are deployed and arranged equidistantly in directions of multiple rotational symmetry axes, the rotational symmetry axes being rotational symmetry axes of a virtual polyhedron that is formed to have a substantial center of the spacecraft as an origin. The tension members support two end portions of two adjacent deployable beam members with tension. The respective end portions of the deployable beam members are simultaneously supported by three or more of the tension members.

Abstract: An artificial satellite system according to the present invention includes first and second artificial satellites. An antenna of the first satellite transmits a radio wave (transmission signal) to the second satellite. An antenna of the second satellite receives the transmission signal. A software defined radio of the second satellite generates a signal having the same frequency and phase as the transmission signal has. The antenna of the second satellite transmits a radio wave of a signal generated by the second satellite to the first satellite. The antenna of the first satellite receives the radio wave (reception signal) transmitted by the second satellite. A data processing device of the first satellite determines a relative distance between the first and second satellites by using the difference between a transmission time of the transmission signal and a reception time of the reception signal and the phase difference between the transmission and reception signals.

Abstract: Provided is a power receiving system having an increased energy conversion efficiency. The power receiving system according to the present disclosure includes a power converter that receives electromagnetic waves transmitted from space and converts the electromagnetic waves into electric power; a thermal energy converter that is disposed adjacent to the power converter and converts thermal energy generated in the power converter; and a controller that controls operation of the thermal energy converter based on an energy intensity distribution of the electromagnetic waves.

Abstract: The space structure control system includes: a space structure; an artificial satellite connected to the space structure; and a propulsion device installed on the artificial satellite and configured to control an orbit and an attitude of the artificial satellite, in which the space structure includes a film-like structure, a solar reflectance control device that controls a spatial pattern of a solar reflectance in a reflecting mirror provided in the film-like structure, and a shape retaining device that is connected to the film-like structure, the propulsion device rotates the film-like structure to generate a centrifugal force, the solar reflectance control device controls a solar reflectance in the reflecting mirror to control a solar radiation pressure to be applied to the reflecting mirror, a three-dimensional shape of the film-like structure is controlled based on the centrifugal force generated by the rotation of the film-like structure and the solar radiation pressure, and the shape of the film-like st

Abstract: An electric-power conversion device receives an electromagnetic wave transmitted from space and converts the electromagnetic wave into electric power. The electric-power conversion device includes: an electric-power conversion portion for receiving an electromagnetic wave transmitted from space and converting the electromagnetic wave into electric power; a propelling device or driving device for moving the electric-power conversion device; a positioning device for determining the position of the electric-power conversion device; a control device for controlling the propelling device or the driving device based on information about the position and the electric power received by the electric-power conversion portion; and an electric-power supply device for supplying the electric power received by the electric-power conversion portion to an electric system.

Abstract: An information processing device includes an input unit for inputting a human influence parameter influenced by a human activity and a natural environment parameter influenced by non-human ecosystem and non-ecosystem activities, a computing unit that calculates a natural capital stock prediction value from the human influence parameter and the natural environment parameter, using a function representing an integration of an amount of change per unit time in natural capital stock, which has elements of internal factors that may change over time and external factors including the human influence parameter and the natural environment parameter, and an output unit for outputting the natural capital stock prediction value calculated by the computing unit.