Abstract: Shows orbit-constellation of satellites that appears virtually geosynchronous.

Abstract: Antenna steering to put an interfering satellite in the null of the main antenna beam.

Abstract: Provided is a system and method for implementing a constellation of satellites in inclined elliptical orbits that provides simplified satellite tracking for ground stations on the earth. The satellite orbits form a pair of repeating ground tracks around the earth. In each ground track the satellites operate only in active arcs well above or below the equator, emulating many of the characteristics of geostationary satellites. The parameters of the satellite orbits are adjusted so that the end points of the active arcs in the two ground tracks coincide; the turn-off point of an active arc in one ground track being the same as the turn-on point of an active arc in the other. For a ground station served by the satellites in these arcs, the active satellites appear to be moving slowly in one direction around a closed, teardrop-shaped path in the sky, at a generally high elevation angle.

Abstract: Provided is an improved system and method for implementing a constellation of satellites in inclined elliptical orbits. The satellites are operated during the portion of their orbits near apogee to emulate the characteristics of geostationary satellites. The orbits are configured to form a number of closely spaced repeating ground tracks around the earth. In each ground track the satellites operate only in arcs well above or below the equator to provide a large number of non-geostationary orbital slots that substantially increase global satellite capacity without interfering with the existing geostationary satellite ring. Minimum spacing is maintained between satellites in each active arc and between satellites in the active arcs of adjacent ground tracks to ensure that the satellites in the non-geostationary constellation do not interfere with each other.

Abstract: A diversity satellite system using a trailer satellite concept. The main satellite is placed into orbit and the trailer satellite, typically a much smaller satellite, is in orbit with the main satellite. The main satellite and trailer satellite are communicating with one another by crosslinks. In this way, two alternative geometric configurations are possible: a first geometric configuration direct from the ground station to the first satellite, and a second geometric configuration to the main satellite from the ground station via the trailer satellite. This enables avoiding interference.

Abstract: An apogee pointed to the sun system which uses an elliptical orbit that is tiled in a way that exploits asymmetry in the Van Allen belts.

Abstract: A satellite communication system that includes a terrestrial base station and a satellite. The satellite communicates with the terrestrial base station using a signal that has a frequency in the range from the S band to visible light. The satellite is configured in a COBRA orbit.

Abstract: Provided is a system and method for implementing a constellation of satellites in inclined elliptical orbits that provides simplified satellite tracking for ground stations on the earth. The satellite orbits form a pair of repeating ground tracks around the earth. In each ground track the satellites operate only in active arcs well above or below the equator, emulating many of the characteristics of geostationary satellites. The parameters of the satellite orbits are adjusted so that the end points of the active arcs in the two ground tracks coincide; the turn-off point of an active arc in one ground track being the same as the turn-on point of an active arc in the other. For a ground station served by the satellites in these arcs, the active satellites appear to be moving slowly in one direction around a closed, teardrop-shaped path in the sky, at a generally high elevation angle.

Abstract: Solar array with movable parts that are faced toward the sun during times of the orbit distant from the debris field. When the orbit is within the debris field, the panels are faced edge on to the direction of the orbit.

Abstract: Array of satellites in a planetary gear arrangement. One ring is circular, and within the other ring, which is elliptical. The circular and elliptical rings overlap at a tangent point. At that point, the satellites are evenly spaced for at least a specified parameter, e.g., time of day or geographical location.

Abstract: A special set of elliptical satellite orbits are described which allow preferential coverage of one parameter over another. According to a first modification, the orbits are retrograde, and preferentially cover one geographical location or time of day as compared with another. A second modification uses prograde orbits and allows the apogee of the orbit to be offset a constant amount with respect to the sun, to thereby cover a different time of day relative to the others. According to a special preferred mode of the invention, the apogee is always pointing towards the sun.

Abstract: A special set of elliptical satellite orbits are described which allow preferential coverage of one parameter over another. According to a first modification, the orbits are retrograde, and preferentially cover one geographical location or time of day as compared with another. A second modification uses prograde orbits and allows the apogee of the orbit to be offset a constant amount with respect to the sun, to thereby cover a different time of day relative to the others. According to a special preferred mode of the invention, the apogee is always pointing towards the sun.

Abstract: An improved, optimized, four-satellite tetrahedral constellation using common period elliptic orbits is disclosed which provides continuous global coverage (i.e., any point on the earth can always maintain line-of-sight visibilty with at least one of the four satellites). The constellation consists of two satellites having perigees in one hemisphere, and two satellites having perigees in the other hemisphere. All satellites have a common period, and positive visibility angles can be maintained down to a constellation (or satellite) period of 27 hours. At higher altitudes (longer periods) both the minimum visibility angles and the mean visibility angles will tend to increase. Replication may be provided by overlaying arrays with convenient offset. The invention is applicable to any celestial body wherein two satellites have two periapses in one hemisphere and the other two satellites have periapses in the other hemisphere.

Abstract: Satellite hemispheric and global coverage with a minimum number of satellites includes a three-satellite elliptic orbit constellation covering the entire Northern (or Southern) Hemisphere and a four-satellite constellation giving continuous global coverage.