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
181	Multi-access laser communications transceiver system	US635856	1990-12-28	US5218467A	1993-06-08	Monte Ross; Donald C. Lokerson; Michael W. Fitzmaurice; Daniel D. Meyer
A satellite system for optical communications such as a multi-access laser transceiver system. Up to six low Earth orbiting satellites send satellite data to a geosynchronous satellite. The data is relayed to a ground station at the Earth's surface. The earth pointing geosynchronous satellite terminal has no gimbal but has a separate tracking mechanism for tracking each low Earth orbiting satellite. The tracking mechanism has a ring assembly rotatable about an axis coaxial with the axis of the field of view of the geosynchronous satellite and a pivotable arm mounted for pivotal movement on the ring assembly. An optical pickup mechanism at the end of each arm is positioned for optical communication with one of the orbiting satellites by rotation of the ring.
182	Method and apparatus for increasing call-handling capacity using a multi-tier satellite network	US08871911	1997-06-12	US06208625B1	2001-03-27	William Frank Zancho; Michael William Krutz; Gregory Barton Vatt
A system for increasing call-handling capacity employs a multi-tier satellite network which includes one or more geosynchronous (GEO) satellites (12) and non-geosynchronous satellites (14). The GEO satellites (12) transfer non delay-sensitive data through the system, while the non-geosynchronous satellites (14) predominantly transfer delay-sensitive data through the system. In a preferred embodiment, a non-geosynchronous satellite (14) receives (102) a data packet, determines (112) whether or not the data packet is delay-sensitive, routes (114) a delay-sensitive data packet through the LEO network, and routes (116) a non delay-sensitive data packet to a GEO satellite (12).
183	Multiple altitude satellite relay system and method	US757542	1996-11-27	US5971324A	1999-10-26	Brian R. Williams; Peter H. Cress
A multiple altitude satellite relay system is disclosed in which Medium Earth Orbit satellites are continuously linked with at least one geosynchronous satellite to provide uninterrupted relaying of messages and data. The Medium Earth Orbit satellites are synchronized with the geosynchronous satellites to produce continuous links. A parameter to achieve the synchronization involves the positions of the Medium Earth Orbit satellite relays relative to the positions of the geosynchronous satellite relays. Another parameter to achieve synchronization involves the ratio between the orbital periods of the geosynchronous satellite relays relative to the orbital periods of the Medium Earth Orbit satellite relays. These parameters may be further adjusted to provide continuous links above the horizon of the earth. An additional satellite relay system is disclosed in which the high-orbit satellite need not be in geosynchronous orbit and in which a high-orbit satellite communicates over a continuous unbroken link with a low-orbit satellite. A further satellite relay system is disclosed in which more than two satellites are arranged at discrete orbit altitudes, again providing a continuous, unbroken daisy-chain link between satellites.
184	INDOOR SATELLITE COMMUNICATION	EP15191389.4	2015-10-26	EP3016300A1	2016-05-04	GUREWITZ, Aaron
A system for obstructed satellite communication, comprising: an outdoor satellite antenna (107) adapted to receive and transmit an electromagnetic satellite signal at a radiation frequency with a geosynchronous satellite, wherein said outdoor satellite antenna is directed towards said geosynchronous satellite along a line of sight; at least one directional antenna (103) adapted to receive and transmit an obstructed electromagnetic signal at same said radiation frequency, wherein each of said at least one directional antenna comprises a feedhorn that is parallel to said line of sight and opposite in direction from said geosynchronous satellite and wherein said at least one directional antenna is adapted to be mounted on a far side of a physical obstruction away from said geosynchronous satellite; and a relay ampl ifi er device (101) adapted to send and receive sai d electromagnetic satellite signal and said obstructed electromagnetic signal between respective said outdoor satellite antenna and said at least one directional antenna; wherein said physical obstruction prevents said electromagnetic satellite signal from being received at an obstructed location on said far side and prevents said obstructed electromagnetic signal originating at said obstructed location from being received by said geosynchronous satellite.
185	Adjustable antenna mount for parabolic antennas	US699577	1985-02-08	US4644365A	1987-02-17	Leonard A. Horning
An antenna mount for aiming a parabolic antenna towards a geosynchronous satellite characterized by four, pivotal sub-assemblies, each of which is rotatable around its own axis. The mount can be quickly adjusted to point the antenna at a particular geosynchronous satellite, or may be caused to sweep across the satellite belt in a scanning manner. The antenna mount can be attached to a support post of virtually any orientation ranging from vertical to horizontal.
186	基于波束常值偏置可共享无线电频谱的方法及低轨通信卫星系统	PCT/CN2020/099137	2020-06-30	WO2021008349A1	2021-01-21	李峰; 侯凤龙; 齐彧; 林骁雄; 裴胜伟; 陈东; 李新刚; 包泽宇
本发明提供一种基于波束常值偏置可与包括地球同步卫星在内的近赤道轨道运行的高轨通信卫星之间共享无线电频谱的方法及低轨通信卫星系统，方法包括：低轨通信卫星在南北极区、赤道附近完成发射波束常值偏置状态的转换，每次实施前后波束偏置方向相反，波束偏置程度为固定的常值；对于临近赤道附近的低轨通信卫星均偏向赤道方向；在北极、南极附近实施波束偏置转换期间，由当前轨道两侧相邻的另外两条轨道内其他低轨通信卫星的波束提供服务。在升交点、降交点附近实施波束偏置转换期间，由位于相同轨道内升交点或降交点另外一侧的相邻低轨通信卫星提供波束覆盖服务。
187	Antenna aperture cover for attenna pointing and improved antenna pointing method using aperture cover	US09852459	2001-05-10	US20020018016A1	2002-02-14	Nick Radonic
An improved apparatus and method for pointing a satellite dish to receive signals from a geo-synchronous satellite. An aperture cover is used to partially block electromagnetic radiation provide to a feed horn and power and/or signal quality measurements are taken with the aperture cover covering various portions of the feed horn opening. Based on these power and/or signal quality measurements, it is determined in what direction and what angle in that direction the satellite dish must be re-oriented to achieve optimal signal strength from a geo-synchronous satellite or other fixed position microwave source.
188	ECCENTRICITY CONTROL FOR GEOSYNCHRONOUS SATELLITES	PCT/US2014038733	2014-05-20	WO2014189893A3	2015-04-02	MAJER VACLAV
Eccentricity control for a geosynchronous satellite includes: setting initial conditions, duration, and schedule for the eccentricity control; defining a plurality of parameters including control loci for centroid, semi-major axis, semi-minor axis, uncontrolled eccentricity radius, right ascension of ascending node, and inclination, wherein the plurality of parameters are defined such that when the eccentricity control is applied, a mean geodetic longitude of the geosynchronous satellite is maintained within a predefined distance from a station longitude.
189	ECCENTRICITY CONTROL FOR GEOSYNCHRONOUS SATELLITES	PCT/US2014/038733	2014-05-20	WO2014189893A2	2014-11-27	MAJER, Vaclav
Eccentricity control for a geosynchronous satellite includes: setting initial conditions, duration, and schedule for the eccentricity control; defining a plurality of parameters including control loci for centroid, semi-major axis, semi-minor axis, uncontrolled eccentricity radius, right ascension of ascending node, and inclination, wherein the plurality of parameters are defined such that when the eccentricity control is applied, a mean geodetic longitude of the geosynchronous satellite is maintained within a predefined distance from a station longitude.
190	Satellite TV dish antenna support	US754414	1985-07-12	US4656486A	1987-04-07	Allan L. Turner
A television dish antenna which is directed toward the geosynchronous satellite orbit must be properly supported so that the antenna dish maintains position for satisfactory television viewing. In addition, the disc must be moved in the proper path so that it may be pointed at other geosynchronous satellites. The dish supporting structure includes a base frame which can be secured to a horizontal surface. The base provides a strong support for pivot bearings carried thereon which permit dish antenna motion along the correct path.
191	ECCENTRICITY CONTROL FOR GEOSYNCHRONOUS SATELLITES	US14282717	2014-05-20	US20140339368A1	2014-11-20	Vaclav Majer
Eccentricity control for a geosynchronous satellite includes: setting initial conditions, duration, and schedule for the eccentricity control; defining a plurality of parameters including control loci for centroid, semi-major axis, semi-minor axis, uncontrolled eccentricity radius, right ascension of ascending node, and inclination, wherein the plurality of parameters are defined such that when the eccentricity control is applied, a mean geodetic longitude of the geosynchronous satellite is maintained within a predefined distance from a station longitude.
192	Precise satellite ranging and timing system using pseudo-noise bandwidth synthesis	US534328	1990-06-04	US5041833A	1991-08-20	Aaron Weinberg
A precise ranging and timing system using pseudo-noise bandwidth synthesis to provide precise orbit determination for geosynchronous and low earth orbit satellites, navigation of low earth orbiting satellite through signals transmitted through geosynchronous satellites and precise time-transfer. The system includes a novel signal structure which is comprised of disjoint, narrow band, spectral components spread over a wide bandwidth. The number of spectral components, their individual bandwidths, and their specific spectral locations over the end-to-end spread bandwidth determine the ultimate capabilities and performance achievable. The broad beam transmission of the precise ranging and timing system signal via a geosynchronous satellite provide the precise ranging and timing system capability to suitably equipped users for a multiplicity of purposes including: (1) precise orbit determination, (2) navigation of low-earth orbiting satellites through signals transmitted through geosynchronous satellites, and (3) precise time transfer.
193	Dispositif de propulsion optimisé pour contrôle d'orbite et contrôle d'attitude de satellite	EP13190390.8	2013-10-25	EP2727844A2	2014-05-07	Celerier, Bruno
L'invention porte sur un dispositif de propulsion pour le contrôle d'orbite d'un satellite à orbite terrestre comprenant une structure (50) dont l'orientation est maintenue constante par rapport à la terre dans une configuration opérationnelle du satellite sur l'orbite; un centre de masse (CM) du satellite étant contenu dans la structure (50) du satellite. Le dispositif de propulsion comprend deux propulseurs (51, 52) aptes à délivrer chacun une poussée selon un axe, et fixés à la structure (50) du satellite dans un même demi-espace séparé par le plan de l'orbite. Les propulseurs (51, 52) sont disposés de part et d'autre d'un plan contenant le centre de masse (CM) et perpendiculaire à un axe Z; les propulseurs (51, 52) étant configurés de manière à ce qu'une force résultante des poussées des deux propulseurs (51, 52) activés simultanément présente une composante majoritaire selon un axe Y du satellite orienté perpendiculairement à l'orbite.
194	Antenna aperture cover for antenna pointing an improved antenna pointing method using aperture cover	US09852459	2001-05-10	US06388614B2	2002-05-14	Nick Radonic
An improved apparatus and method for pointing a satellite dish to receive signals from a geo-synchronous satellite. An aperture cover is used to partially block electromagnetic radiation provide to a feed horn and power and/or signal quality measurements are taken with the aperture cover covering various portions of the feed horn opening. Based on these power and/or signal quality measurements, it is determined in what direction and what angle in that direction the satellite dish must be re-oriented to achieve optimal signal strength from a geo-synchronous satellite or other fixed position microwave source.
195	강우 강도 산출 방법 및 이를 수행하는 장치	KR20160086223	2016-07-07	KR20180005915A	2018-01-17	SHIN DONG BIN
이하, 강우강도를산출하는방법이개시된다. 실시예에따른강우강도산출방법은정지궤도위성에탑재된적외센서의밝기온도에기초하여산출된밝기온도차이를이용하여구름유형을분류하는단계; 및분류된구름유형에대응하는데이터베이스에기초하여강우강도를산출하는단계를포함할수 있다.
196	선박기준국 추가에 의한 SBAS 시스템을 위한 정지 궤도 위성의 정밀 궤도 결정 방법	KR1020160043418	2016-04-08	KR1020170115786A	2017-10-18	이상욱; 신천식
본발명은 SBAS 시스템을위한정지궤도위성의정밀궤도결정방법및 통제국및 선박기준국에관한것이다. 본발명에따르면, 협역기준국으로부터상기협역기준국이상기정지궤도위성으로부터수신한 SBAS 보정데이터와레인징데이터및 상기협역기준국의위치데이터를수신하는단계; 선박기준국으로부터상기선박기준국이상기정지궤도위성으로부터수신한 SBAS 보정데이터와레인징데이터및 상기선박기준국의위치데이터를수신하는단계; 및상기협역기준국으로부터수신한 SBAS 보정데이터와레인징데이터, 상기협역기준국의위치데이터, 상기선박기준국으로부터수신한 SBAS 보정데이터와레인징데이터및 상기선박기준국의위치데이터를이용하여최상의 DOP를이루는기준국레인징정보로상기정지궤도위성의궤도를결정하는단계를포함하는정지궤도위성의정밀궤도결정방법이제공된다.
197	System for global earth navigation using inclined geosynchronous orbit satellite	US13333333	2011-08-07	US20120168566A1	2012-07-05	Byoung Sun LEE; Yoo La HWANG; Jae Hoon KIM
A global earth navigation satellite system may be provided. The global earth navigation satellite system may include a group of satellites including at least one inclined geosynchronous satellite disposed in at least one orbital plane distinguished based on an interval determined based on a longitudinal coordinate of the earth, and the at least one inclined geosynchronous satellite may be disposed in the at least one orbital plane at predetermined intervals, and may revolve around the earth at a predetermined inclination of satellite orbit so as to provide, over time, geometric shape change information associated with the earth, geometric shape change information associated with a low earth orbit satellite, and geometric shape change information associated with a geostationary satellite.
198	METHOD AND DEVICE FOR ADJUSTING SATELLITE ANTENNAS	PCT/DE1999/003114	1999-09-28	WO00024082A1	2000-04-27
The invention relates to a device for adjusting antennas situated on geostationary satellites and to a corresponding method carried out with this device. According to the invention, the device has its own antenna, which uses the existing reflector system to enable an exact adjustment to be carried out with the help of a ground station located outside of the terrestrial footprint of the main antenna.
199	COMPACT SATCOM ANTENNA WITH INTEGRATED LNA	US11462398	2006-08-04	US20080030408A1	2008-02-07	Chad Coates; David L. Dunathan; Stephen Darnell Hughey; Malcolm Packer; Kurt Alan Zimmerman; Brent Eric Raiber
A compact SATCOM antenna is provided having an LNA integrated into the radiator body which may be mounted to a handheld satellite radio and articulated with respect to the radio to assume a wide variety of positions for communication with a geosynchronous satellite.
200	일체형 저소음 증폭기(ＬＮＡ)를 구비한 소형 위성통신 안테나	KR1020097003806	2007-08-01	KR1020090038468A	2009-04-20	코츠,차드; 두나단,데이비드엘.; 허그헤이,스테판다넬; 팩커,말콤; 짐머만,커트,알란; 라이버,브렌트,에릭
A compact SATCOM antenna is provided having an LNA integrated into the radiator body which may be mounted to a handheld satellite radio and articulated with respect to the radio to assume a wide variety of positions for communication with a geosynchronous satellite.

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