Apogee at constant time-of-day equatorial (ACE) orbit
AssigneeSpace Systems/Loral, Inc.
InventorAndrew E. Turner
Life of this patent
Estimating the term…
Abstract
A man-made satellite (1) traveling in an elliptical orbit. The orbit has five or six daily apogees, which are positioned above the same longitudes of the earth at substantially the same local time-of-day for each day of the year. The longitudes and times-of-day can be preselected subject only to the proviso that they be equispaced. The apsidal rotation rate in inertial space (ARRIS) of the orbit is substantially equal to the mean rate at which the earth revolves about the sun. The orbit is preferably equatorial, in order to simplify ground tracking and to maximize the impact of the apsidal rotation.
Claims16
A man-made satellite that is made to travel in an elliptical orbit about the earth, wherein:
- the satellite revolves about the earth a discrete number of times per day;
- each of the apogees corresponding to the daily revolutions is positioned over the same earth longitude at substantially the same local time-of-day for each day of the year;
- and
- the apsidal rotation rate in inertial space of the orbit is substantially equal to the mean rate at which the earth revolves about the sun.
A method for placing a man-made satellite into an elliptical orbit about the earth, said orbit having a discrete number of daily apogees, each apogee positioned over the same earth longitude at substantially the same local time-of-day for each day of the year, said method comprising the step of:
- causing the apsidal rotation rate in inertial space of the orbit to be substantially equal to the mean rate at which the earth revolves about the sun.
Dependencies are inferred from the claim text.