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
41	静止衛星のための離心率制御	JP2016515003	2014-05-20	JP2016525978A	2016-09-01	マイヤー，バルカフ
静止衛星のための離心率制御は、離心率制御のための初期条件、持続時間、およびスケジュールを設定することと、重心、長半径、短半径、離心率無制御時の動径、昇交点赤経、および傾斜角のための制御軌跡を含む複数のパラメータを規定することとを含み、複数のパラメータが、離心率が制御される場合、静止衛星の平均測地経度が、基地局経度から既定の距離内に維持されるように規定される。【選択図】図1
42	GEOSYNCHRONOUS SATELLITE CONSTELLATION	EP06800053.8	2006-07-13	EP1955449B1	2013-09-04	JACOMB-HOOD, Anthony W.; BROWN, David

43	Système de positionnement d'un satellite géostationnaire	EP11167878.5	2011-05-27	EP2392940A3	2013-06-12	Celerier, Bruno
L'invention concerne un système de positionnement d'un satellite géostationnaire (1), comprenant : - au moins quatre stations sol chacune étant de position connue et apte à envoyer vers le satellite (1) un signal dit signal montant, - et des moyens de mesure des différences des temps d'arrivée au satellite des signaux montants.
44	GEOSYNCHRONOUS SATELLITE CONSTELLATION	EP06800053.8	2006-07-13	EP1955449A2	2008-08-13	JACOMB-HOOD, Anthony W.; BROWN, David
A satellite communications system is described for increasing capacity through spectrum reuse by multiple satellites. The system includes a constellation of satellites traveling in a geosynchronous orbit, where the geosynchronous orbit defines a satellite track- The satellite track of the constellation overlaps a geostationary orbital location occupied by a legacy satellite traveling in a geostationary orbit. To prevent interference between the co- located constellation and legacy satellite, each of the constellation satellites operates in a silent mode when traveling within an interference beam width of a ground terminal in communication with the legacy satellite. Once outside of the interference beam width, the constellation satellites return to an active mode of operation.
45	ECCENTRICITY CONTROL FOR GEOSYNCHRONOUS SATELLITES	EP14748001.6	2014-05-20	EP2999630A2	2016-03-30	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.
46	Area navigational system using geosynchronous satellites	US133005	1980-03-24	US4472720A	1984-09-18	Thomas W. Reesor
An area navigational system using geosynchronous satellites is disclosed. The navigational system comprises a master satellite and seven slave satellites uniformly disposed in geosynchronous orbit above the equator of the earth. The master satellite comprises a master tone oscillator producing a reference tone which is transmitted to the immediate neighboring slave satellites which in turn, serially relays the reference tone to the remaining slave satellites such that each slave satellite receives the reference tone. Each slave satellite comprises a slave tone oscillator which is synchronized by the reference tone to be in phase with the phase of the master tone oscillator. The output of the master tone oscillator and the slave tone oscillators are frequency modulated and transmitted to the earth. A receiver on a mobile craft receives three of such transmissions and demodulates the carrier frequencies to recover the three tones. The phases of the tones are compared with one another to obtain two hyperbolic lines of positions whose intersection defines the position of the mobile craft. The foregoing abstract is merely a resume of one general application, is not a complete discussion of all principles of operation or applications, and is not to be construed as a limitation on the scope of the claimed subject matter.
47	Transmitting apparatus for use in non-geostationary satellites	EP95117089.3	1995-10-30	EP0709288B1	1999-07-14	Ikebe, Kenichi, c/o NEC Corp.

48	Orbital Determination (OD) Of Geosynchronous Satellites	US14453474	2014-08-06	US20160041267A1	2016-02-11	Ian S. Robinson
Technology for determining an orbit of a geosynchronous satellite is described. A ground station can receive a transponded (RF) signal from a relay satellite. The relay satellite can receive an RF signal from the geosynchronous satellite and transpond the RF signal to create the transponded RF signal. The ground station can identify a second Doppler shift associated with the transponded RF signal received at the ground station from the relay satellite. The RF signal received at the relay satellite from the geosynchronous satellite can be associated with a first Doppler shift. The ground station can determine a frequency of the transponded RF signal received at the ground station from the relay satellite. The first Doppler shift associated with the RF signal transmitted from the geosynchronous satellite to the relay satellite can be calculated using the frequency of the transponded RF signal and the second Doppler shift associated with the transponded signal. The orbit of the geosynchronous satellite can be determined based on the first Doppler shift associated with the RF signal.
49	Elliptical satellite system which emulates the characteristics of geosynchronous satellites	US09546098	2000-04-10	US06611683B1	2003-08-26	David Castiel; John Draim; Kenneth F. Manning
An elliptical satellite system which carries out communication. The satellite orbits a height above the earth less than that necessary for geosynchronous orbits. When the satellite is near the apogee portion of its orbit, its velocity approximates the rotational velocity of the earth, and during that period it appears to hover over the earth. Each ground station on the earth always communicates a satellite within a predetermined position of its apogee, and hence that satellite appears to the ground station to hover over the earth. The satellite hence does not communicate with any earth station when it is outside of that apogee portion. During the times when the satellite is outside the apogee portion, its communication is therefore shut off to prevent.any possibility of interfering with geosynchronous satellites. During this time, the power supply on the satellite is also used to charge a battery on the satellite. This enables the power supply to be made smaller by an amount equivalent to the duty cycle of the satellite: during the time which it is on.
50	Elliptical satellite system which emulates the characteristics of geosynchronous satellites	US09892132	2001-06-25	US20010051521A1	2001-12-13	David Castiel; John Draim; Kenneth F. Manning
An elliptical satellite communication system including a constellation of satellites which orbit the earth at a height less than that necessary for geosynchronous orbits but which simulate the characteristics of geosynchronous orbits. The satellites' velocity near the apogee portion of their orbit approximates the rotational velocity of the earth, and during that period appear to hover over the earth. The ground stations on the earth always communicate with a satellite at or near its apogee, and hence that satellite appears to the ground station to hover over the earth. During the times when the satellite is outside the apogee portion, its communication is shut off to prevent any possibility of interfering with geosynchronous satellites and its power supply is used to charge a battery on the satellite. Thus, the power supply of the system can be reduced by an amount equivalent to the percentage of time the satellite is not used.
51	Ellipitical satellite system which emulates the characteristics of geosychronous satellites	US54303	1998-04-02	US5957409A	1999-09-28	David Castiel; John Draim; Kenneth F. Manning
An elliptical satellite system which carries out communication. The satellite orbits a height above the earth less than that necessary for geosynchronous orbits. When the satellite is near the apogee portion of its orbit, its velocity approximates the rotational velocity of the earth, and during that period it appears to hover over the earth. Each ground station on the earth always communicates a satellite within a predetermined position of its apogee, and hence that satellite appears to the ground station to hover over the earth. The satellite hence does not communicate with any earth station when it is outside of that apogee portion. During the times when the satellite is outside the apogee portion, its communication is therefore shut off to prevent any possibility of interfering with geosynchronous satellites. During this time, the power supply on the satellite is also used to charge a battery on the satellite. This enables the power supply to be made smaller by an amount equivalent to the duty cycle of the satellite: during the time which it is on.
52	GPS overlay system for a geostationary satellite	EP96115578.5	1996-09-27	EP0766097B1	1999-03-03	Kawano, Shuichi, K.K. Toshiba

53	Satellite géostationnaire à accumulateurs d'énergie électrique	EP94402233.4	1994-10-05	EP0647559B1	1996-12-18	Faisant, Pierre Philippe

54	Transmitting apparatus for use in non-geostationary satellites	EP95117089.3	1995-10-30	EP0709288A3	1996-07-31	Ikebe, Kenichi, c/o NEC Corp.
A transmitting apparatus for use in non-geostationary satellites which allows compliance with the restrictions placed on PFD even when the Earth is located between the geostationary satellite and the non-geostationary satellite. The transmitting apparatus 10 for use in non-geostationary satellites having a transmitting section 16 which sends a transmitting signal to the geostationary satellite, comprises an Earth-sensing section 19 for detecting the presence of the Earth in the direction of transmission and a transmission direction-shifting section 20 for shifting the direction of transmission of the transmitting signal in response to detection of the Earth-sensing section 19 to prevent the Earth from being exposed to the transmitting signal. Instead of the transmission direction-shifting section 20, there may be used a power supply-suspending section which automatically suspends power supply to the transmitting section 16 thereby stopping transmission of the transmitting signal.
55	Elliptical satellite system which emulates the characteristics of geosynchronous satellites	US409808	1995-03-24	US5845206A	1998-12-01	David Castiel; John Draim; Kenneth F. Manning
An elliptical satellite system which carries out communication. The satellite orbits a height above the earth less than that necessary for geosynchronous orbits. When the satellite is near the apogee portion of its orbit, its velocity approximates the rotational velocity of the earth, and during that period it appears to hover over the earth. Each ground station on the earth always communicates with a satellite within a predetermined position of its apogee, and hence that satellite appears to the ground station to hover over the earth. The satellite hence does not communicate with any earth station when it is outside of that apogee portion. During the times when the satellite is outside the apogee portion, its communication is therefore shut off to prevent any possibility of interfering with geosynchronous satellites. During this time, the power supply on the satellite is also used to charge a battery on the satellite. This enables the power supply to be made smaller by an amount equivalent to the duty cycle of the satellite: during the time which it is on.
56	Coordinatable system of inclined geosynchronous satellite orbits	US09444199	1999-11-19	US06325332B1	2001-12-04	Alfred Cellier; Raul D. Rey
A coordinatable system of geosynchronous (24-hour), inclined, and slightly elliptical satellite orbits enables spectrum re-use by forming “highways” of moving “slots” in the latitudes above and below the geostationary (GSO) belt worldwide. Each of a plurality of repeating ground tracks is shared by multiple satellite orbits (and thus slots). These are phased to achieve minimum specified angular separation from other slots using the same frequencies. Ground track (and thus orbital) parameters are chosen to realize specified shapes and are located at specified longitudes of symmetry to maximize the total number of slots. Consideration is given to specified constraints on service area coverage, elevation angle, and time coverage.
57	Dispositif de contrôle d'attitude d'un satellite géostationnaire	EP03292442.5	2003-10-03	EP1413940B1	2010-02-17	Montfort, Eric; Salenc, Cédric, La palme d'Or; Roser, Xavier; Gaudic, Loic

58	Geosynchronous hub communications satelite and system	EP97300677.8	1997-02-04	EP0788246A3	1999-06-02	Hargis, Keith J.
A satellite communications system includes hub satellite (111) which are equipped to communicate with at least three other satellites. The hub satellites include crosslink interfaces (100) for each of the other satellites with which it may communicate and a switching system (106) for routing those communications between interfaces. A system of a given number of satellites may include several hubs and may be configured in a way which permits any satellite within the system to communicate with a hub either directly or after transiting one or more intervening satellites. Systems which include fewer hubs may require communication with more than one intervening satellite before a hub is reached.
59	Attitude pointing error correction system and method for geosynchronous satellites	US44327	1987-04-30	US4911385A	1990-03-27	Brij N. Agrawal; Pierre J. Madon
A system and method for attitude control in a geosynchronous satellite to compensate for roll and yaw pointing errors consequent to orbit inclination variation from the nominal equatorial orbit plane provides for an inertially fixed momentum vector coupled to the satellite through a gimbal system providing a one and preferably two degree-of-freedom relationship with the momentum vector. In a two degree-of-freedom embodiment, the momentum vector is established by spinning the satellite about an axis or providing an independent momentum wheel with the gimbal axes provided along the roll and yaw axes. Gimbal torquers torque the satellite about the inertially fixed momentum vector in a time-varying manner to effect correction of the roll and yaw pointing errors. Roll and yaw pointing errors consequent to orbit inclination drift from the nominal equatorial orbit are corrected in a fuel-efficient manner to extend the operating life of the satellite.
60	Elliptical satellite system which emulates the characteristics of geosynchronous satellites	US09775786	2001-02-01	US06577864B2	2003-06-10	David Castiel; John Draim; Kenneth F. Manning
An elliptical satellite system which carries out communication. The satellite orbits a height above the earth less than that necessary for geosynchronous orbits. When the satellite is near the apogee portion of its orbit, its velocity approximates the rotational velocity of the earth, and during that period it appears to hover over the earth. Each ground station on the earth always communicates a satellite within a predetermined position of its apogee, and hence that satellite appears to the ground station to hover over the earth. The satellite hence does not communicate with any earth station when it is outside of that apogee portion. During the times when the satellite is outside the apogee portion, its communication is therefore shut off to prevent any possibility of interfering with geosynchronous satellites. During this time, the power supply on the satellite is also used to charge a battery on the satellite. This enables the power supply to be made smaller by an amount equivalent to the duty cycle of the satellite: during the time which it is on.

1 2 3 4 5 6 7 8 9 10

IPRDB

热门服务

关于我们

友情链接

联系方式