会员体验
专利管家(专利管理)
工作空间(专利管理)
风险监控(情报监控)
数据分析(专利分析)
侵权分析(诉讼无效)
联系我们
交流群
官方交流:
QQ群: 891211   
微信请扫码    >>>
现在联系顾问~
首页 / 专利库 / 人造卫星 / 专利数据
序号 专利名 申请号 申请日 公开(公告)号 公开(公告)日 发明人
101 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.
102 Maneuver device for artificial satellite US10078109 2002-02-20 US06622969B2 2003-09-23 Toshiaki Yamashita
The present invention provides a maneuver device for an artificial satellite, which causes small attitude error during maneuver and which requires a shorter period of setting time for obtaining a target attitude. The maneuver device is provided with: a feed forward torque instruction signal generator 8 which outputs a feed forward torque instruction signal 11 based on a maneuver plan; a thruster 10 which outputs control torque based on the feed forward torque instruction signal 11; and an attitude control signal calculator 6 to which an attitude angle and an angular velocity of the artificial satellite as well as a target attitude angle and a target angular velocity are input and which outputs an attitude control signal 13. The maneuver device is further provided with a disturbance compensating signal calculator to which the feed forward torque instruction signal 11 and a detected angular velocity signal 16 are input, and which generates and outputs a disturbance compensating signal 12. The maneuver device is yet further provided with a reaction wheel 7 which generates control torque based on the attitude control signal 13 and the disturbance compensating signal 12.
103 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.
104 Artificial satellite communication system US886228 1992-05-21 US5871181A 1999-02-16 Jonathan Mass
A communication system including a constellation of a plurality of artificial satellites orbiting the Earth, each artificial satellite having communication apparatus providing communication with the Earth, characterized in that the plurality of artificial satellites are in triply-geosynchronous (TGS) orbits having a period of eight sidereal hours, or twice-triply-geosynchronous (TTGS) orbits having a period of sixteen sidereal hours, which orbits are inclined with respect to the Equator and synchronized with the Earth's rotation such as to exploit the natural spacing of approximately 120.degree. in longitude of the major land masses of Europe, North America and the Far East for communication with the artificial satellites to provide for higher elevation angles in such land masses than in other areas.
105 人工衛星の自律運用計画システムおよび人工衛星の運用計画装置 PCT/JP2017/025908 2017-07-18 WO2018016471A1 2018-01-25 西山 岳宏; 北村 憲司

衛星側に衛星側運用パラメータ記憶部22、運用計画部23を備え、地上側に地上側運用パラメータ設定部11、衛星側の運用パラメータ記憶部と同じ運用パラメータを記憶する地上側運用パラメータ記憶部12、衛星側の運用計画部と同一の機能を有する運用計画推定部14を備え、地上側運用パラメータ設定部11において運用計画に用いる運用パラメータを決定し、地上側運用パラメータ記憶部12と衛星側運用パラメータ記憶部22に随時アップロードし、地上側の運用計画推測部14と衛星側の運用計画部23が同一の運用パラメータに基づいてそれぞれ運用計画を作成する。

106 Ergonomically designed check-out counter system for supermarket and merchandising industries EP90300123.8 1990-01-05 EP0396218A1 1990-11-07 Vrooman, Carll DeWitt; Taylor, Dennis Ray

An ergonomically designed check-out counter system for supermarket and merchandising industries is characterised by provisions for differences in human heights, hand and position of operators and for ease in handling of merchandise to reduce fatigue and injury to the operators while providing maximum productivity under both light and heavy through put requirements. The check-out counter system includes one or more of the features of a housing defining the overall shape of the check-out counter system, a movable floor device (27) for receiving the cashier and for moving vertically up and down to position the cashier at a desired height regardless of the human height of the cashier, a movable chair device (40) positioned in the intermediate opening (24) for receiving the cashier and including adjustment devices (41,43) for moving the chair vertically and horizontally to desired positions thereby providing the cashier with the option of sitting or standing, a keyboard device (50) for entering price data of the merchandise which may be moved back and forth to accommodate right-handed and left-handed cashiers, and merchandise bagging devices (60,61,70,73) for easy handling and bagging of the merchandise after checking-­out by the cashier and providing for direct bagging by the cashier or bagging by a bagger.

107 人工衛星用太陽光発電翼及び人工衛星 JP2015065659 2015-03-27 JP2015189469A 2015-11-02 クラウス・ジンメルマン; レネ・モイラー; トマス・フェッファーコーン; イェンス・ビルケル
【課題】簡明な手段により、輸送時にソーラーパネルが確実に支持されるようにした、人工衛星用太陽光発電翼を提供する。
【解決手段】少なくとも2枚の剛性ソーラーパネル14、16と少なくとも1枚の半剛性ソーラーパネル18、20とを含む複数枚のソーラーパネルを備え、それら複数枚のソーラーパネル14〜20が稼働時形態と輸送時形態とを取り得るように互いに連結されている人工衛星用太陽光発電翼10が記載されている。前記輸送時形態にあるときに前記複数枚のソーラーパネル14〜20が互いに重ね合わされた状態で保持されており、また、前記輸送時形態にあるときに前記半剛性ソーラーパネル18、20は自由振動可能な状態で2枚の前記剛性ソーラーパネル14、16の間に位置している。更に、少なくとも1つの人工衛星用太陽光発電翼10を備えた人工衛星が記載されている。
【選択図】図1
108 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.
109 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.
110 利用人造衛星的信號收信方法、服務提供方法、人造衛星之控制方法、收信終端以及人造衛星控制裝置 TW092127841 2003-10-07 TW200412050A 2004-07-01 岩田忠良; 前田利秀; 石田隆張; 井上秀樹
〔課題〕防止品質劣化,在服務區域之任何地區中,都能夠由適合於通訊、廣播之仰角的衛星接受服務之提供。〔解決手段〕通信、廣播系統1係透過由衛星管制局2所控制的人造衛星之環繞衛星3,在通信、廣播中心局4和位於波束波點5內之移動台6或固定台7之間,進行通信服務及/或廣播服務的通信、廣播系統。藉由在可保持高的衛星仰角之時間帶進行此環繞衛星的切換,以防止通訊、廣播的品質劣化。
111 人工衛星の軌道面制御方法 PCT/JP2014/051228 2014-01-22 WO2014115753A1 2014-07-31 小泉 宏之; 青山 順一

【課題】主衛星のミッションを損なうことなく、しかも人工衛星の小型化及び軽量化を図った上で高い推力レベルの推進装置を備えた人工衛星と実質的に同等な軌道制御を実現することが可能な人工衛星の軌道面制御方法を提供することを目的とする。 【解決手段】主衛星と共に打ち上げられる複数の小型の人工衛星11,12をそれぞれの目的軌道へ投入する人工衛星の軌道面制御方法であり、主衛星の目的軌道S1に投入された小型の人工衛星11,12を低い推力レベルの推進装置を用いて軌道高度を変更させ、当該軌道高度における地球重力場の扁平性に起因する軌道面の遷移を利用して複数の人工衛星11,12をそれぞれの目的軌道S5,S9へ投入することを特徴とするものである。

112 Composite material for artificial satellite, frame for artificial satellite, and panel for artificial satellite JP2012226068 2012-10-11 JP2014076750A 2014-05-01 OKUYAMA KEIICHI; YAMAGUCHI KOJI; SATO RYOICHI
PROBLEM TO BE SOLVED: To provide a lightweight and inexpensive heat insulation material for an artificial satellite used for a small-sized or extremely small-sized artificial satellite showing a severe temperature gradient, and capable of controlling the temperature of a loaded apparatus within a required range.SOLUTION: This heat insulation material is used in a small-sized or extremely small-sized artificial satellite showing a severe temperature gradient. The heat insulation material is mainly composed of an aromatic polyimide in which an aromatic compound is directly bonded with an imide bond. The aromatic polyimide contains carbon fibers. The carbon fibers have a wire diameter of 7 μm and a length of 130 μm. The coefficient of thermal conductivity λ is changed according to the mixing ratio of the carbon fibers.
113 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.
114 인공위성용 힌지 장치 KR1020080007065 2008-01-23 KR100942172B1 2010-02-12 박희창; 김병인; 이성휘; 김진희; 김경원; 김선원; 김규선; 진익민; 이상률; 이주진
본 발명은 인공위성용 힌지 장치에 관한 것으로서, 더욱 상세하게는 우주공간의 극한환경(극 고온, 극저온현상)에서도 인공위성에서 태양전지판이 원활히 전개되고, 인공위성이 우주선에 실려 우주로 쏘아 올려질 때 발생되는 진동에도 잘 견디며, 상기 태양전지판의 완전 전개되어 우주공간에서 비행시, 발생되는 진동 및 충격 등에도 잘 견디는 특징이 있다. 이와 같이, 본 발명은 우주공간의 극한환경에서도 태양전지판이 전개되도록 인공위성과 태양전지판을 연결하거나 태양전지판과 태양전지판을 연결하는 힌지부에 있어서, 상기 인공위성 또는 태양전지판의 일단부에 결합부재에 의해 부착되는 제 1플레이트와; 상기 태양전지판의 일단부에 결합부재에 의해 부착되되, 상기 제 1플레이트와 끝단부가 축에 의해 결합되어 태양전지판을 전개시키는 제 2플레이트와; 상기 제 1플레이트와 제 2플레이트에 상호 연결되어 제 1플레이트와 제 2플레이트를 탄성적으로 전개되도록 형성된 인장 스프링을 포함하여 구성되는 것을 특징으로 하는 특징이 있다. 인공위성, 태양전지판, 힌지장치, 플레이트, 인장 스프링
115 SATELLITE ARTIFICIEL ET PROCÉDÉ DE REMPLISSAGE D'UN RÉSERVOIR DE GAZ PROPULSIF DUDIT SATELLITE ARTIFICIEL EP16705226.5 2016-01-22 EP3212503B1 2017-11-22 WALKER, Andrew, Nicholas
116 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).

117 Attitude determination system for artificial satellite US919193 1997-08-28 US6102338A 2000-08-15 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.
118 Artificial satellite attitude control system US606660 1984-05-03 US4617634A 1986-10-14 Kiichiro Izumida; Ritaroh Kasai
A system for controlling an attitude of an artificial satellite to decide the present attitude of the satellite on a spatial coordinate and angular velocities of rotation about body axes of the satellite, by the use of inertial sensors and star sensors, to calculate an objective attitude of the satellite on the basis of the present attitude information, the angular velocities of rotation about the body axes and orbit information received from a ground station so that the attitude of the satellite and the changing rate thereof are controlled simultaneously.
119 PROPULSION SYSTEM FOR SMALL ARTIFICIAL SATELLITES PCT/EP2016/067680 2016-07-25 WO2017021191A1 2017-02-09 ROSSETTINI, Luca; ALBANO LOPES, Gonçalo Daniel

A propulsion system for small artificial satellites comprises a plurality of engines (2) fixable to a frame (101) of a satellite (100); a control unit (3) connected functionally to the engines (2) for sending at least one activation signal (AS) for activating at least one engine (2); the system is selectively configurable at least between a first configuration in which at least one of the engines (2) is activated for correcting the orbit of the satellite (100) and a second configuration in which at least one of the engines (2) is activated for dispersing said satellite (100) relative to another adjacent satellite.

120 METHOD AND APPARATUS FOR CHANGING ORBIT OF ARTIFICIAL SATELLITE PCT/JP1989000819 1989-08-11 WO1990001447A1 1990-02-22 NIPPON TELEGRAPH AND TELEPHONE CORPORATION
The method and apparatus for changing the orbit of an artificial satellite in accordance with the present invention comprises causing an orbit changing device (1) to approach a target satellite (2) in a space, combining them, forming a dumb-bell like combination system, generating propelling force in the orbit changing device to generate simultaneously an orbit speed increment and rotation around the gravitational center to the gravitational center of the combination system so as to put the combination system onto a transition orbit (02), cutting off the combination system at a timing at which the axial direction of the combination system becomes perpendicular to the speed vector on the transition orbit, putting the target satellite on a final target orbit (03) and putting the orbit changing device thus cut off on an orbit different from that of the target satellite.