人造卫星相关的专利数据

序号	专利名	申请号	申请日	公开（公告）号	公开（公告）日	发明人
81	인공위성용 힌지 장치	KR1020080007065	2008-01-23	KR1020090081139A	2009-07-28	박희창; 김병인; 이성휘; 김진희; 김경원; 김선원; 김규선; 진익민; 이상률; 이주진
A hinge apparatus for an artificial satellite is provided to spread a solar panel smoothly in an artificial satellite in the extreme environment of outer space, to bear the vibration occurring when putting an artificial satellite loaded on a spacecraft into the sky, and to bear the vibration and impact occurring when flying in the outer space after a solar panel is spread completely. A hinge apparatus(60) for an artificial satellite comprises a first plate(10) attached to one end of an artificial satellite or a solar panel by a coupling member, a second plate(20) attached to one end of the solar panel by a coupling member and coupled with the first plate by a shaft to spread the solar panel, and a tension spring(30) coupled between the first plate and the second plate to spread the first plate and the second plate elastically.
82	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.
83	PANEL TYPE ARTIFICIAL SATELLITE AND ARTIFICIAL SATELLITE SYSTEM THEREWITH	US13096078	2011-04-28	US20110278399A1	2011-11-17	Tadayuki TAKAHASHI; Takeshi Takashima; Hiroyuki Ogawa; Shin-ichiro Sakai; Naoko Iwata; Yoshikatsu Kuroda; Kazunori Masukawa
An artificial satellite system 200 comprises at least two panel type artificial satellites 100 closely connected with a plurality kind of multi networks and the minimum necessary essential tools for one artificial satellite installed on a substrate of each panel type artificial satellites 100, wherein the multi networks are formed by a communicating network for communicating data among data processing tools installed on each the panel type artificial satellites 100, a heat pipe for providing thermal energy among tools installed on each the panel type artificial satellites 100 and a battery supplying line for connecting battery controlling devices installed in the each panel type artificial satellite so that the artificial satellite system 200 can maintain higher and various controlling performance with a back-up effect of the multi network in the case that any function tool is damaged in one of the panel type artificial satellite 100.
84	SATELLITE ARTIFICIEL	EP16763906.1	2016-08-10	EP3259188A1	2017-12-27	CAEL, Philippe; WALKER, Andrew; MENA, Fabrice
The invention concerns an artificial satellite comprising one face from the North face and the South face supporting at least one main radiator (42, 44) having an outer face turned towards space and an inner face opposite the outer face. The satellite comprises a bearing structure carrying the North face, the South face, the East face and the West face. At least one part (54, 56) of said at least one main radiator (42, 44) protrudes from at least one face from the East face and the West face (36). The inner face of said at least one protruding part (54, 56) is covered with a high infrared emissivity material. The value of the dimension (L54,56) of said at least one protruding part (54, 56) is between 19% and 50% of the value of the distance (Lc) between the East and West faces.
85	Artificial satellites	US3568192D	1966-10-24	US3568192A	1971-03-02	DAWSON THOMAS WILLIAM GRANT
A very light, easily dispensed, efficient and durable passive radial communication satellite comprising a filamentary netlike structure of which alternate lengths of the filaments are metal coated to comprise dipoles, and in which those surfaces of the net filaments between the metal covered dipole regions are covered with a layer of metal which affords protection against damage to the net by long-wavelength ultraviolet radiation and reduces the rate of evaporation of the net material, said layer of metal being of small thickness compared to that forming the dipoles so that radio wave reflection therefrom is negligible.
86	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。
87	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	TWI227973B	2005-02-11	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。
88	人造衛星天線	TW077305887	1988-10-11	TW119026S	1989-09-11	派崔克.坎貝爾.亨特

89	Panel type artificial satellite and artificial satellite system therewith	EP11165796.1	2011-05-12	EP2386489A2	2011-11-16	Takahashi, Tadayuki; Takashima, Takeshi; Ogawa, Hiroyuki; Sakai, Shin-ichiro; Iwata, Naoko; Kuroda, Yoshikatsu; Masukawa, Kazunori
An artificial satellite system (200) comprises at least two panel type artificial satellites (100) closely connected with a plurality kind of multi networks and the minimum necessary essential tools for one artificial satellite installed on a substrate of each panel type artificial satellites (100), wherein the multi networks(N1, N2, N3) are formed by a communicating network for communicating data among data processing tools installed on each the panel type artificial satellites (100), a heat pipe for providing thermal energy among tools installed on each the panel type artificial satellites (100) and a battery supplying line for connecting battery controlling devices installed in the each panel type artificial satellite so that the artificial satellite system (200) can maintain higher and various controlling performance with a back-up effect of the multi network in the case that any function tool is damaged in one of the panel type artificial satellite (100).
90	Maneuver device for artificial satellite	US10078109	2002-02-20	US20020148930A1	2002-10-17	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.
91	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.
92	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.
93	ERGONOMIC SEATING ASSEMBLIES AND METHODS	PCT/US2012/049599	2012-08-03	WO2013020088A2	2013-02-07	CHRISTIANSON, Nicholas, M.; GOMREE, Jean Francois; SCHOENFELDER, Rodney, C.; WEBER, Jeffrey; MONITOR, Shawn
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 arc 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.
94	Sandwich panel, and structural panel of artificial satellite	JP2004170138	2004-06-08	JP2005349874A	2005-12-22	HAHN STEVEN; UMADONO SHINJI; USAMI AKIRA; YAMAMOTO KAZUYUKI; OZAKI TAKESHI
PROBLEM TO BE SOLVED: To provide a circuit built-in sandwich panel consisting of a first skin, a second skin, and a core located between these two skins which is coexistent with a conventional surface mount of an electronic instrument or the like, capable of realizing integration and consolidation with the instrument, and a structure of a wire harness, a satellite or the like, and reducing the size, weight, and cost of the satellite, and a structural panel of the artificial satellite. SOLUTION: At least one (4a, 4b) of components or elements of an electronic circuit or an optical circuit and instruments related thereto is arranged in spaces (2a, 2b) provided in advance inside a core 8 located between two skins (1A, 1B). COPYRIGHT: (C)2006,JPO&NCIPI
95	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.
96	アンテナ内蔵型人工衛星	PCT/JP2012/078134	2012-10-31	WO2013065722A1	2013-05-10	森口　達次
人工衛星は、そのデッドスペースに接する当該人工衛星の壁に形成された少なくとも１つのハッチと、ハッチを開くハッチ開閉機構と、を備え、ハッチにアンテナが取付けられている。
97	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.
98	Simulated orbiting artificial satellite	US72607958	1958-04-03	US2897607A	1959-08-04	PARK ALEXANDER C

99	Magnetic bearing arrangement for an artificial satellite	US469659	1983-02-25	US4483570A	1984-11-20	Masao Inoue
A magnetic bearing arrangement for rotor for controlling the attitude of an artificial satellite wherein the rotor has a rotating speed and an axis of rotation which are adjusted in accordance with a change in the attitude of the satellite. The arrangement includes a stator defined by at least three segments, and each stator segment is provided with a permanent magnet to eliminate the necessity of any electromagnet for controlling radial rotor displacement and any sensor for detecting such radial displacement. The apparatus is free from any eddy currents that may cause great resistance to rotation.
100	MAN-MADE SATELLITE WITH AERODYNAMIC CONTROL VANES	PCT/FR1994000480	1994-04-27	WO1994025344A1	1994-11-10	CENTRE NATIONAL D'ETUDES SPATIALES
Man-made satellite with roll, yaw and pitch control vanes (4, 4', 5) for applying rotational torques to the satellite about its three axes by means of the resistance of the rarefied air surrounding the satellite (dynamic inertia compensation for rotating objects aboard the satellite can also be effected). This invention applies particularly to low orbit satellites.

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