地球同步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	Argument of perigee correction with longitude control for inclined, eccentric, geosynchronous satellites	US09588858	2000-06-06	US06317661B1	2001-11-13	Michael J. Bruno; Brian Kemper; Sherry Pervan
A method of controlling the orbit of an inclined, eccentric geosynchronous satellite by maintaining its perigee location while simultaneously preventing a reference point on the orbit from moving too far relative to a normal position over the Earth. Doing this changes the semimajor axis of the orbit, which when perturbed away from the geosynchronous value, creates a drift rate relative to the Earth. To correct the argument of perigee and maintain the prescribed tolerance on ground track position, multiple maneuvers must be performed to control the drift rate. The relationship between maximum allowable velocity change and time between maneuvers is defined by the required correction to the argument of perigee and the allowable motion of the reference point.
82	SYSTEM AND METHOD FOR IMPLEMENTING TERMINAL TO TERMINAL CONNECTIONS VIA A GEOSYNCHRONOUS EARTH ORBIT SATELLITE	EP98935674.6	1998-07-13	EP0925657B1	2011-06-08	JOSHI, Chandra; NOERPEL, Anthony, R.; TEWARI, Neeraj; STELZER, Gerard, P.; ROOS, David; SU, Chi-Jiun
An approach for immediate channel assignment in a wireless communications system involves receiving a channel request message from a wireless transceiver, the channel request message including a dialed party number; forming an immediate assignment message including a channel assignment; transmitting the immediate assignment message to the wireless transceiver; and establishing a communications channel between the wireless transceiver and a called party by establishing a channel between the wireless transceiver and the called party.
83	Radio frequency broadcasting systems and methods using two low-cost geosynchronous satellites and hemispherical coverage antennas	US227045	1994-04-13	US5485485A	1996-01-16	Robert D. Briskman; John M. Seavey; Paul Medeiros
The methods and systems for reducing multipath fading and outage from blockage in a radio broadcasting system that is adapted to simultaneously broadcast signals having frequencies in the range of about 300 MHz to about 3,000 MHz from two or more satellite sources traveling on a substantially geosynchronous orbit with the satellite sources separated from one another by a sufficient distance to minimize outage from physical blockages and multipath fading of signals from these satellites and received by a plurality of fixed and mobile platforms using substantially flat, hemispherical coverage antennas, each antenna having an outer diameter no greater than about 10 inches and each adapted to receive frequencies in the range of about 300 MHz to about 3,000 MHz.
84	Elliptical satellite system emulating characteristics of geosynchronous satellites during the apogee portion of an elliptical orbit	US09235942	1999-01-22	US06795687B1	2004-09-21	David Castiel; John Draim; Kenneth F. Manning
An array of satellites which is virtually geosynchronous. Each satellite is in an elliptical orbit. The apogee portion of each elliptical orbit is over one of the regions of interest. Each satellite is virtually geosynchronous during its apogee portion, over the region of interest. When it leaves the apogee portion, the satellite goes to another of the regions of interest, and acts virtually geosynchronous over that region.
85	Agencement d'antenne pour la réception de signaux émis par un satellite géostationnaire	EP00401511.1	2000-05-29	EP1058125B1	2011-07-06	Tits, Daniel G.; Lotfy, Kamal

86	Method of operating a geostationary satellite and satellite control system for implementing said method	EP06290705.0	2006-05-03	EP1852350A1	2007-11-07	Rogers, Colin EUTELSAT; Bellido, Eduardo EUTELSAT; Pattinson, Lindsay Robert EUTELSAT
The present invention relates to a method of operating a geostationary satellite and to a satellite control system for implementing said method. The method comprises a step of bringing the satellite at the end of its lifetime, i.e. in the absence of chemical reaction, to a disposal orbit by providing thrust through initially very small but frequent thruster firings allowing the residuals of the mono-propellant or bi-propellant to be expelled in a controlled manner.
87	Method of operating a geostationary satellite and satellite control system for implementing said method	EP06290705.0	2006-05-03	EP1852350B1	2009-07-22	Rogers, Colin EUTELSAT; Bellido, Eduardo EUTELSAT; Pattinson, Lindsay Robert EUTELSAT

88	Method for controlling east/west motion of a geostationary satellite	EP91300174.9	1991-01-10	EP0438229B1	1998-03-18	White, Lisa K.,; Gamble, Donald W.; Kelly, Thomas J.; Bingaman, Ronald H.

89	SYSTEM AND METHOD FOR IMPLEMENTING TERMINAL TO TERMINAL CONNECTIONS VIA A GEOSYNCHRONOUS EARTH ORBIT SATELLITE	EP98935674.0	1998-07-13	EP0925657A1	1999-06-30	JOSHI, Chandra; NOERPEL, Anthony, R.; TEWARI, Neeraj; STELZER, Gerard, P.; ROOS, David; SU, Chi-Jiun
An approach for immediate channel assignment in a wireless communications system involves receiving a channel request message from a wireless transceiver, the channel request message including a dialed party number; forming an immediate assignment message including a channel assignment; transmitting the immediate assignment message to the wireless transceiver; and establishing a communications channel between the wireless transceiver and a called party by establishing a channel between the wireless transceiver and the called party.
90	An orbit raising system and method for geosynchronous satellites	EP00304391.6	2000-05-24	EP1059232A3	2001-08-29	Gelon, Walter; Kamel, Ahmed; Stratemeier, Darren; Hur-Diaz, Sun
A satellite (11) is launched that contains high thrust chemical propulsion thrusters, high specific impulse electric propulsion thrusters and a solar array. The satellite quickly escapes the Van Allen radiation belts by firing the high thrust chemical propulsion thrusters at apogees of intermediate orbits, staffing from the transfer orbit (14) initiated by a launch vehicle, to successively raise the perigees until the perigee clears the Van Allen radiation belts. The payload mass and mission life are maximized by firing high specific impulse electric propulsion thrusters to raise the satellite to near synchronous orbit, while steering the thrust vector and solar array to maintain the sun's illumination on the solar array. The chemical and/or electric propulsion thrusters are then fired to achieve geosynchronous orbit (15).
91	航空機ベースの空対地通信システムおよび既存の静止衛星サービスの間でシェアしているスペクトル	JP2014518931	2012-06-26	JP5946528B2	2016-07-06	クルーズ,ジョセフ・エム; ウォルシュ,パトリック・ジェイ; トビン,ジョセフ・エイ; ジョイス,ティム; リウ,ヨン; チャリ,アナンド・ケイ; コスタニク,イヴィカ; サロカ,ハロルド・ジー

92	An orbit raising system and method for geosynchronous satellites	EP00304391.6	2000-05-24	EP1059232A2	2000-12-13	Gelon, Walter; Kamel, Ahmed; Stratemeier, Darren; Hur-Diaz, Sun
A satellite (11) is launched that contains high thrust chemical propulsion thrusters, high specific impulse electric propulsion thrusters and a solar array. The satellite quickly escapes the Van Allen radiation belts by firing the high thrust chemical propulsion thrusters at apogees of intermediate orbits, staffing from the transfer orbit (14) initiated by a launch vehicle, to successively raise the perigees until the perigee clears the Van Allen radiation belts. The payload mass and mission life are maximized by firing high specific impulse electric propulsion thrusters to raise the satellite to near synchronous orbit, while steering the thrust vector and solar array to maintain the sun's illumination on the solar array. The chemical and/or electric propulsion thrusters are then fired to achieve geosynchronous orbit (15).
93	DISPOSITIF DE PRESSURISATION D'UN SOUS-SYSTEME DE PROPULSION BILIQUIDE UNIFIE D'UN SATELLITE GEOSTATIONNAIRE	EP96904890.0	1996-02-21	EP0810946A1	1997-12-10	DELEPIERRE-MASSUE, Olivier; FEVRIER, Claude; SALOME, Roland; LE TORRIVELLEC, Pierre
A device for pressurising a unified two-liquid propulsion subsystem for geostationary satellites, including a high-pressure helium storage assembly (10) comprising at least one helium storage tank, a control assembly (11) and an assembly for pressurising propellant tanks (17, 18) interconnected through a pressurising circuit. The control assembly is an electronic control assembly including at least one solenoid valve (51) arranged at one point in the pressurising circuit and controlled by a processing and control circuit (54) receiving data from pressure sensors (43, 47, 48) for the various tanks. Said processing and control circuit enables the propellant tanks (17, 18) to be pressurised at a constant pressure during the satellite transition and position-fixing process, while enabling the amount of residual propellants to be measured during the orbital operating time of the satellite.
94	地球同步衛星反向鏈路之附加項頻道的解碼 DECODING OF THE OVERHEAD CHANNELS OF THE GEO SATELLITE REVERSE LINK	TW096141020	2007-10-31	TW200838161A	2008-09-16	史肯特賈亞曼 JAYARAMAN, SRIKANT; 南宮濬 NAMGOONG, JUNE
使用一種高功率效率技術來解調變一地球同步(GEO)衛星上行鏈路之經編碼之附加項頻道。一用於一無線通信系統中之相干接收器能夠藉由自擷取自一導頻信號之碼字實現頻道估計來判定在該附加項頻道中傳送之資訊。建立一組有效碼字。自一導頻信號擷取導頻符號,且自該導頻信號進行一頻道估計。使該組有效碼字中之碼字相關且移除該等信號中之一頻道相位模糊性,且選擇一具有最大相關之碼字。使用該所選擇碼字來產生一經修正之頻道估計。
95	Virtual polar satellite ground station for low orbit earth observation satellites based on a geostationary satellite pointing an antenna over an earth pole	EP09290542.1	2009-07-06	EP2273692A1	2011-01-12	Agnew, Martin; Hegyi, akos; Kinsella, Francis; Renouard, Laurent
The invention relates to a satellite system comprising a satellite operating in an orbit around the Earth and a satellite operating in another orbit around the Earth; where the satellite points a fixed beam at least temporarily to a zone above the Earth's surface through which the satellite passes.
96	DISPOSITIF DE PRESSURISATION D'UN SOUS-SYSTEME DE PROPULSION BILIQUIDE UNIFIE D'UN SATELLITE GEOSTATIONNAIRE	EP96904890.9	1996-02-21	EP0810946B1	1998-11-18	DELEPIERRE-MASSUE, Olivier; FEVRIER, Claude; SALOME, Roland; LE TORRIVELLEC, Pierre
A device for pressurising a unified two-liquid propulsion subsystem for geostationary satellites, including a high-pressure helium storage assembly (10) comprising at least one helium storage tank, a control assembly (11) and an assembly for pressurising propellant tanks (17, 18) interconnected through a pressurising circuit. The control assembly is an electronic control assembly including at least one solenoid valve (51) arranged at one point in the pressurising circuit and controlled by a processing and control circuit (54) receiving data from pressure sensors (43, 47, 48) for the various tanks. Said processing and control circuit enables the propellant tanks (17, 18) to be pressurised at a constant pressure during the satellite transition and position-fixing process, while enabling the amount of residual propellants to be measured during the orbital operating time of the satellite.
97	用於利用尾咬碼之地球同步衛星反向鏈路之接收器 RECIEVER FOR THE GEO SATELLITE REVERSE LINK USING TAIL-BITING CODE	TW096141019	2007-10-31	TW200835171A	2008-08-16	史肯特賈亞曼 JAYARAMAN, SRIKANT; 南宮濬 NAMGOONG, JUNE
本發明描述一種用於地球同步(GEO)衛星反向鏈路之接收器及用以解決頻道估計問題的方法,該接收器利用尾咬迴旋碼用於錯誤控制。利用導頻頻道而在每一狀態處跳躍地開始該頻道估計。利用分支度量計算用於對該尾咬迴旋碼之循環解碼。該技術在實施部分尾咬時為有效的。
98	Virtual polar satellite ground station for low orbit earth observation satellites based on a geostationary satellite pointing an antenna over an earth pole	EP09290542.1	2009-07-06	EP2273692B1	2016-08-31	Agnew, Martin; Hegyi, akos; Kinsella, Francis; Renouard, Laurent
The invention relates to a satellite system comprising a satellite operating in an orbit around the Earth and a satellite operating in another orbit around the Earth; where the satellite points a fixed beam at least temporarily to a zone above the Earth's surface through which the satellite passes.
99	2개의 위성들의 빔들 내에 로케이팅되고 인터넷 접속 포인트(IPP)의 이용가능성에 따라 제 1 위성으로부터 제 2 위성으로 데이터를 중계하는 중계 노드를 갖는 비-정지 위성 네트워크에서의 통신을 위한 방법	KR1020167008587	2014-09-03	KR101749636B1	2017-06-21	잘랄리,아흐매드; 아메스,윌리엄지핀
본개시내용은비-정지궤도(NGSO) 위성네트워크에서의통신들을위한방법및 장치를제시한다. 예를들어, 방법은, 중계노드에서 NGSO 위성네트워크의제 1 NGSO 위성으로부터데이터를수신하는단계― 중계노드는 NGSO 위성네트워크의제 1 위성및 제 2 위성과연관된경계또는공통빔 영역에로케이팅되고, 데이터는, 제 1 NGSO 위성과연관된복수의빔들중 적어도하나에서인터넷접속포인트(IPP)가이용가능하지않다고제 1 NGSO 위성에의해식별되는것에대한응답으로중계노드에서수신됨―, 및중계노드로부터 NGSO 위성네트워크의제 2 NGSO 위성으로데이터를중계하는단계를포함할수 있으며, 여기서, IPP는제 2 NGSO 위성과연관된복수의빔들중 적어도하나에서이용가능하다. 그러므로, 비-정지궤도(NGSO) 위성네트워크에서의통신들이달성될수 있다.
100	多高度卫星中继系统和方法	CN96113079.2	1996-10-03	CN1099773C	2003-01-22	布列恩·R·威廉姆斯; 彼特·H·克莱思
披露了一种多高度卫星中继系统，其中中地轨道卫星和至少一个地球同步卫星形成链路，以便提供不间断的信息和数据的中继通信。中地轨道卫星和地球同步卫星同步，从而产生连续的链路。实现所述同步的参数涉及中地轨道卫星中继站和地球同步卫星中继站的相对位置。实现同步的另一个参数涉及地球同步卫星中继站的轨道周期和中地轨道卫星中继站的轨道周期的比。这些参数可以被进一步调整，从而在地球的地平线上方提供连续的链路。

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