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公开(公告)号：US20180128675A1
公开(公告)日：2018-05-10
申请号：US15575563
申请日：2016-04-27
Applicant: HITACHI, LTD.
Inventor： Yosuke TANABE , Masanori WATANABE , Naoki YONEYA
Abstract: A problem of the present invention is to provide a vibration analysis program capable of analyzing bidirectional exchanges between a distribution amount and a difference amount with respect to an external system of the part in a part modeled as a finite element, in which the difference amount accumulation characteristic and the distribution amount accumulation characteristic are distributed. A vibration analysis program of the present invention includes a first step 6 of importing a finite element model of a target part modeled by a finite element method program 4 to calculate an accumulation characteristic matrix and connection matrix, a second step 8 of calculating a difference amount-distribution amount mode matrix and eigenvectors after inputting 7 an attenuation characteristic to the accumulation characteristic matrix or the connection matrix as necessary, and a third step 14 of importing an input difference amount-flow amount vector to a target part obtained from an external system simulator 9, performing a mode coordinate transformation of the input difference amount-flow amount vector, calculating the mode vector response, and performing physical coordinate transformation of mode vector.
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公开(公告)号：US20250136299A1
公开(公告)日：2025-05-01
申请号：US18923918
申请日：2024-10-23
Applicant: Hitachi, Ltd.
Inventor： Koichi WATANABE , Tsukasa FUNANE , Makoto ITO , Yosuke TANABE , Hisatoshi KIMURA
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
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公开(公告)号：US20240322752A1
公开(公告)日：2024-09-26
申请号：US18678131
申请日：2024-05-30
Applicant: Hitachi, Ltd.
Inventor： Tsukasa FUNANE , Koichi WATANABE , Yosuke TANABE , Jun HAYAKAWA
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.
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公开(公告)号：US20250110197A1
公开(公告)日：2025-04-03
申请号：US18887231
申请日：2024-09-17
Applicant: Hitachi, Ltd.
Inventor： Tsukasa FUNANE , Yosuke TANABE , Hisatoshi KIMURA , Makoto ITO , Koichi WATANABE
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.
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Patent Agency Ranking
公开(公告)号：US20240308697A1
公开(公告)日：2024-09-19
申请号：US18584242
申请日：2024-02-22
Applicant: Hitachi, Ltd.
Inventor： Makoto ITO , Tsukasa FUNANE , Koichi WATANABE , Yosuke TANABE , Hisatoshi KIMURA
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 structure is retained or stabilized by the shape retaining device.
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公开(公告)号：US20250002177A1
公开(公告)日：2025-01-02
申请号：US18594564
申请日：2024-03-04
Applicant: Hitachi, Ltd.
Inventor： Yosuke TANABE , Tsukasa FUNANE , Koichi WATANABE , Hisatoshi KIMURA , Makoto ITO
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.
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7.发明公开公开(公告)号：US20240340078A1
公开(公告)日：2024-10-10
申请号：US18596139
申请日：2024-03-05
Applicant: Hitachi, Ltd.
Inventor： Hisatoshi KIMURA , Tsukasa FUNANE , Yosuke TANABE , Makoto ITO , Koichi WATANABE
CPC classification number: H04B7/18521 , B64G1/40 , H04B7/18526 , H04W64/006
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.
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8.发明公开公开(公告)号：US20240162760A1
公开(公告)日：2024-05-16
申请号：US18507319
申请日：2023-11-13
Applicant: Hitachi, Ltd.
Inventor： Makoto ITO , Koichi WATANABE , Tsukasa FUNANE , Yosuke TANABE , Hisatoshi KIMURA , Keiji WATANABE
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.
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公开(公告)号：US20230412124A1
公开(公告)日：2023-12-21
申请号：US18112752
申请日：2023-02-22
Applicant: Hitachi, Ltd.
Inventor： Tsukasa FUNANE , Koichi WATANABE , Yosuke TANABE , Jun HAYAKAWA
IPC: H02S40/44
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.
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