| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 121 | Procédé de mise sur orbite d'un satellite artificiel | EP82400781.9 | 1982-04-29 | EP0064917B1 | 1985-07-31 | Barkats, Gérard; Morel, Charles |
| 122 | 筐体構造および人工衛星 | PCT/JP2017/002500 | 2017-01-25 | WO2017150016A1 | 2017-09-08 | 佐藤 積利; 松澤 廉 |
筐体構造は第一の電子部品の収容空間を形成する。前記筐体構造は、互いに平行に配置される複数の支柱と、前記複数の支柱間に設けられ、外壁を構成する複数のパネルと、を備える。前記複数のパネルのうちの少なくとも一つのパネルは、その外面に前記第一の電子部品と接続される第二の電子部品が設けられるパネルであり、前記複数のパネルは、前記複数の支柱に対して分離可能に取り付けられる。 |
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| 123 | ERGONOMIC SEATING ASSEMBLIES AND METHODS | PCT/US2012049599 | 2012-08-03 | WO2013020088A3 | 2013-06-13 | CHRISTIANSON NICHOLAS M; GOMREE JEAN FRANCOIS; SCHOENFELDER RODNEY C; WEBER JEFFREY; MONITOR SHAWN |
| Seating assemblies and methods are disclosed. A seating assembly (100) can comprise a seat, a back support (114), and a frame component (110). The frame component can extend from a bottom portion (118), positioned near an underside of the seat, to a top portion (120), configured to maintain the back support at a position above the seat. The back support can laterally extend from a left edge portion (1670) to a right edge portion (1672) and can include a spring member (122) at or near each of the left and right edge portions. The spring member can include at least one undulation or arc (1674) providing integrated compression adaptation to a user. The seating assembly can further comprise a tilt mechanism (408), engaged with the frame component, including one or more leaf springs (424) and a spring contact assembly. The spring contact assembly (426) can be positioned on a top side of the one or more leaf springs. | ||||||
| 124 | SATELLITE ARTIFICIEL ET PROCÉDÉ DE REMPLISSAGE D'UN RÉSERVOIR DE GAZ PROPULSIF DUDIT SATELLITE ARTIFICIEL | PCT/FR2016/050136 | 2016-01-22 | WO2016120547A1 | 2016-08-04 | WALKER, Andrew, Nicholas |
L'invention concerne un satellite artificiel comportant : - une structure-support portant des murs porte-équipements, - un adaptateur-lanceur solidaire de la structure-support, - un premier radiateur (26), - au moins un premier équipement de transport de chaleur (42) par fluide comportant au moins une conduite (44) ayant une première section d'échange thermique (50) et une seconde section d'échange thermique (52), ladite seconde section d'échange thermique (52) étant propre à être en contact thermique avec ledit premier radiateur(26), caractérisé en ce que ladite première section d'échange thermique (50) est en contact thermique avec au moins une partie de l'adaptateur-lanceur (16). L'invention concerne également procédé de remplissage d'un réservoir de gaz propulsif dudit satellite artificiel. |
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| 125 | ERGONOMIC SEATING ASSEMBLIES AND METHODS | US15261543 | 2016-09-09 | US20170065087A1 | 2017-03-09 | Nicholas M. Christianson; Jean Francois Gomrée; Rodney C. Schoenfelder; Jeffrey Weber; Shawn Monitor |
| Seating assemblies and methods are disclosed. A seating assembly can comprise a seat, a back support, and a frame component. The frame component can extend from a bottom portion, positioned near an underside of the seat, to a top portion, configured to maintain the back support at a position above the seat. The back support can laterally extend from a left edge portion to a right edge portion and can include a spring member at or near each of the left and right edge portions. The spring member can include at least one undulation or are providing integrated compression adaptation to a user. The seating assembly can further comprise a tilt mechanism, engaged with the frame component, including one or more leaf springs and a spring contact assembly. The spring contact assembly can be positioned on a top side of the one or more leaf springs. | ||||||
| 126 | ARTIFICIAL SATELLITE WITH INTEGRATED ANTENNA | US14353543 | 2012-10-31 | US20140292594A1 | 2014-10-02 | Tatsuji Moriguchi |
| An artificial satellite includes at least one hatch formed in a wall of the artificial satellite coming in contact with dead space of the artificial satellite, and a hatch opening and closing mechanism which opens the hatch, and the antenna is attached to the hatch. | ||||||
| 127 | ERGONOMIC SEATING ASSEMBLIES AND METHODS | US14235847 | 2012-08-03 | US20140239686A1 | 2014-08-28 | Nicholas M. Christianson; Jean Francois Gomrée; Rodney C. Schoenfelder; Jeffrey Weber; Shawn Monitor |
| Seating assemblies and methods are disclosed. A seating assembly (100) can comprise a seat, a back support (114), and a frame component (110). The frame component can extend from a bottom portion (118), positioned near an underside of the seat, to a top portion (120), configured to maintain the back support at a position above the seat. The back support can laterally extend from a left edge portion (1670) to a right edge portion (1672) and can include a spring member (122) at or near each of the left and right edge portions. The spring member can include at least one undulation or arc (1674) providing integrated rated compression adaptation to a user. The seating assembly can further comprise a tilt mechanism (408), engaged with the frame component, including one or more leaf springs (424) and a spring contact assembly. The spring contact assembly (426) can be positioned on a top side of the one or more leaf springs. | ||||||
| 128 | Simulated orbiting artificial satellite | US72607958 | 1958-04-03 | US2897607A | 1959-08-04 | PARK ALEXANDER C |
| 129 | ARTIFICIAL SATELLITE WITH INTEGRATED ANTENNA | EP12845914 | 2012-10-31 | EP2774856A4 | 2015-06-24 | MORIGUCHI TATSUJI |
| 130 | METHOD AND APPARATUS FOR CHANGING ORBIT OF ARTIFICIAL SATELLITE | EP89909248 | 1989-08-11 | EP0382858A4 | 1991-03-13 | YASAKA, TETSUO |
| 131 | 摸高器（人造卫星） | CN202330511662.5 | 2023-08-11 | CN308547842S | 2024-03-29 | 范峰 |
| 1.本外观设计产品的名称：摸高器（人造卫星）。 2.本外观设计产品的用途：本外观设计产品用于身高尺中，将游标底部置于被测量者的头顶，用于测量出被测量者的身高。 3.本外观设计产品的设计要点：在于形状与图案的结合。 4.最能表明设计要点的图片或照片：立体图1。 | ||||||
| 132 | 정지궤도 인공위성 피라미드형 반작용휠 모멘텀 관리 방법 | KR1020020058621 | 2002-09-27 | KR1020040026961A | 2004-04-01 | 박영웅 |
| PURPOSE: Pyramid-type reaction wheel momentum management algorithm of a geostationary orbit artificial satellite is provided to automatically manage the reaction wheel algorithm by separately discriminating the momentum management algorithm at a dumping mode and a station keeping mode. CONSTITUTION: Pyramid-type reaction wheel momentum(W1,W2,W3,W4) management algorithm of a geostationary orbit artificial satellite automatically manages steps of deciding dumping execution by separating a stable region and a normal operation range for the current reaction wheel momentum, separately considering a thruster set for four reaction wheels, and then deciding a thruster set adequate to produce torque in 3-axis directions. At a station keeping mode, the pyramid-type reaction wheel momentum management algorithm of the geostationary orbit artificial satellite calculates a torque value to be controlled for disturbance, decides the dumping state when the reaction wheel momentum is not in the stable region, and executes attitude control, using reaction wheels when the torque direction to be controlled and the torque direction to be dumped are not coincided. | ||||||
| 133 | 인공 위성을 이용한 광고전광판 운영 장치 및 방법 | KR1020000043564 | 2000-07-28 | KR1020020009915A | 2002-02-02 | 박승한; 김학중 |
| PURPOSE: An apparatus and a method for managing an electrical advertisement board by using an artificial satellite are provided to easily control the advertisement draft of the advertisement board, and to cope effectively and rapidly with an emergency situation of the advertisement board. CONSTITUTION: The apparatus for managing a movable electrical advertisement board(400) and a fixed electrical advertisement board(500) by using an artificial satellite(300) comprises a wire-line/wire-less terminal(100), a central control part(200), a translater(600), a wire-line phone(700), and a personal terminal(800). The movable advertisement board has a shock detection part, a manipulation part, a movable advertisement board condition inspection part, a control part, a display part, a communication part, and a location tracking sender/receiver. The fixed advertisement board has a manipulation part, a control part, a display part, and a communication part. | ||||||
| 134 | Artificial satellite equipment panel | US11534684 | 2006-09-25 | US07619326B2 | 2009-11-17 | Hajime Takeya; Tsuyoshi Ozaki; Hirotsugu Morinaga; Shinji Badono |
| A satellite equipment panel on which may be mounted an installation equipment of a predetermined function, connectable by an interface, constitutes an artificial satellite. The satellite equipment panel includes a panel body, at least two interfaces for an interconnection to another satellite equipment panel, a line transfer switch disposed within the panel body for line transferring of the interconnection between the interfaces, wiring disposed within the panel body and connected at one end to one of the interfaces and at the other end to the line transfer switch for interconnecting the interfaces on that panel body. The interfaces and the wiring, in cooperation with a support structure, constitute a wiring module disposed within the panel body. The interface may comprise at least one of interfaces of electric communication, optical communication, and optical sensor. | ||||||
| 135 | Attitude detection system for artificial satellite | US10189906 | 2002-07-02 | US06725133B2 | 2004-04-20 | Toshiaki Yamashita |
| An attitude detection system for an artificial satellite includes an interpolator for interpolating an angular-velocity signal to generate an interpolated angular-velocity signal, a sequential Kalman filter for generating a low-frequency attitude-angle signal, and an adder for adding the low-frequency attitude-angle signal and a high-frequency attitude-angle signal generated by a high-frequency angular sensor to generate a broad-band attitude-angle signal. | ||||||
| 136 | Attitude detection system for artificial satellite | US10189906 | 2002-07-02 | US20030004620A1 | 2003-01-02 | Toshiaki Yamashita |
| An attitude detection system for an artificial satellite includes an interpolator for interpolating an angular-velocity signal to generate an interpolated angular-velocity signal, a sequential Kalman filter for generating a low-frequency attitude-angle signal, and an adder for adding the low-frequency attitude-angle signal and a high-frequency attitude-angle signal generated by a high-frequency angular sensor to generate a broad-band attitude-angle signal. | ||||||
| 137 | Attitude determination system for artificial satellite | US09610603 | 2000-07-05 | US06227496B1 | 2001-05-08 | Shoji Yoshikawa; Katsuhiko Yamada; Hiroshi Sakashita; Hiroo Yonechi |
| An attitude determination system for an artificial satellite capable of performing star identification without need for the aid of ground station includes an image processing module (17) for processing star images observed at predetermined time points by a star sensor (16) mounted on the artificial satellite (1) for arithmetically determining direction vectors of the observed stars, a rotation estimating module (18) for estimating a rotational motion of the artificial satellite (1) between an attitude of the artificial satellite at a predetermined time point and an attitude of the artificial satellite at another time point, an elongation estimating module (19) for estimating elongations between the direction vectors of plural stars the images of which are picked up at a same time point by the star sensor and estimating the elongations between the direction vectors of plural stars the images of which are picked up at different time points by the star sensor on the basis of the estimated rotational motion, a star identifying module (20) for establishing correspondences between a plurality of the stars for which relation of the elongation has been determined and stars on a star catalog for identifying the stars, and an attitude angle estimating module (21) for estimating an attitude angle of the artificial satellite on the basis of result of identification of the stars. | ||||||
| 138 | Weather modification by artificial satellites | US69655 | 1998-04-28 | US5984239A | 1999-11-16 | Franklin Y. K. Chen |
| A Satellite Weather Modification System (SWMS) uses earth satellites to harness solar energy to modify the thermodynamics and composition of the earth's atmosphere. SWMS has three subsystems: The first subsystem includes a network of earth satellites called Satellite Engines (SEs) used to reflect solar energy and/or transform solar energy into other forms of energy beams discharged at specified locations. The media at these locations and the media through which the energy beams pass absorb these energies and change them into heat. The second subsystem includes a large network of Remote Sensing Devices (RSDs). These sensors are used to measure local media compositions, dynamic parameters and thermodynamic properties. Sensor measurements are fed back to the third subsystem, which includes a network of Ground Control Stations (GCSs). GCSs provide energy beam guidance by estimating each beam's characteristics and its aim point trajectory as functions of time. Integration of these three subsystems establishes a sensor feedback energy beam guidance and control loop. SWMS's weather modification applications include alteration of precipitation, reclaiming of wasteland, reducing damage by bad weather, and improving environment. Its non-weather related applications include supplying concentrated energy to electricity generating stations (solar, wind and hydro), high latitude greenhouse farms, and solar powered airplanes. | ||||||
| 139 | PARTICLE BEAM TREATMENT SYSTEM, AND BEAM POSITION CORRECTION METHOD THEREFOR | EP12848652.9 | 2012-09-21 | EP2777766A1 | 2014-09-17 | HANAKAWA, Kazushi; SUGAHARA, Kengo; ODAWARA, Shuhei; HARADA, Hisashi; IKEDA, Masahiro; OTANI, Toshihiro; HONDA, Taizo; YOSHIDA, Katsuhisa |
A particle beam treatment system includes an accelerator system (2) that accelerates a charged particle beam and a beam transport system (3) that transports a high-energy beam emitted from the accelerator to an irradiation location, wherein the beam transport system (3) is provided with at least one steering electromagnet (33) and at least one beam position monitor (34) corresponding to the at least one steering electromagnet (33), and wherein the at least one beam position monitor (34) supplies an excitation current for correcting a beam position, which periodically varies, to the at least one steering electromagnet (33). |
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| 140 | ARTIFICIAL SATELLITE EQUIPMENT PANEL | US11534684 | 2006-09-25 | US20070221786A1 | 2007-09-27 | Hajime TAKEYA; Tsuyoshi OZAKI; Hirotsugu MORINAGA; Shinji BADONO |
| A satellite equipment panel on which may be mounted an installation equipment of a predetermined function, connectable by an interface, constitutes an artificial satellite. The satellite equipment panel includes a panel body, at least two interfaces for an interconnection to another satellite equipment panel, a line transfer switch disposed within the panel body for line transferring of the interconnection between the interfaces, a wiring disposed within the panel body and connected at one end to one of the interfaces and at the other end to the line transfer switch for interconnecting the interfaces on that panel body. The interfaces and the wiring, in cooperation with a support structure, constitute a wiring module disposed within the panel body. The interface may comprise at least one of interfaces of electric communication, optical communication, and optical sensor. | ||||||
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