US5326054A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Apogee at constant time-of-day equatorial (ACE) orbit
Assignee: Lanteris Space LLC
•
Filing: 1988-01-21
•
Granted: 1994-07-05
•
Expires: 2008-01-21
Abstract
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.
Inventors
- 👤 Andrew E. Turner
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-06 16:36
CPC Classifications
B; B64; B64G; B64G1/00; B64G1/22; B64G1/24; B64G1/242; B64G1/10; B64G1/1007
Claims Analysis
Total Claims: 18
Claim 1
Independent Claim
83 words
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.
Claim 2
Dependent Claim
83 words
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.
Claim 3
Dependent Claim
17 words
The satellite of claim 1 wherein the orbit lies substantially in the plane containing the earth's equator.
Claim 4
Dependent Claim
16 words
The satellite of claim 1 wherein the satellite revolves about the earth five times per day.
Claim 5
Dependent Claim
26 words
The satellite of claim 3 in which the semi-major axis of the orbit is approximately 14,450 km; and the eccentricity of the orbit is approximately 0.49.
Claim 6
Dependent Claim
23 words
The satellite of claim 3 wherein the orbit's apogee radius is approximately 21,480 km; and the orbit's perigee radius is approximately 7,410 km.
Claim 7
Dependent Claim
21 words
The satellite of claim 3 wherein the five daily apogees are positioned above any set of five preselected equispaced earth longitudes.
Claim 8
Dependent Claim
30 words
The satellite of claim 1 wherein the orbit follows substantially the same angular path each day of the year from the point of view of any point on the earth.
Claim 9
Dependent Claim
16 words
The satellite of claim 1 wherein the satellite revolves about the earth six times per day.
Claim 10
Dependent Claim
26 words
The satellite of claim 8 in which the semi-major axis of the orbit is approximately 12,775 km; and the eccentricity of the orbit is approximately 0.23.
Claim 11
Dependent Claim
23 words
The satellite of claim 8 wherein the orbit's apogee radius is approximately 15,710 km; and the orbit's perigee radius is approximately 9,840 km.
Claim 12
Dependent Claim
21 words
The satellite of claim 8 wherein the six daily apogees are positioned above any set of six preselected equispaced earth longitudes.
Claim 13
Dependent Claim
29 words
The satellite of claim 1 wherein said satellite communicates with several tracking stations located on the earth, each tracking station having an antenna adapted to point towards the satellite.
Claim 14
Independent Claim
76 words
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.
Claim 15
Independent Claim
76 words
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.
Claim 16
Dependent Claim
39 words
The method of claim 13 further comprising the step of periodically performing a stationkeeping maneuver on the satellite to keep at least one of the parameters from the set of parameters comprising inclination and eccentricity within a preselected deadband.
Claim 17
Dependent Claim
81 words
The method of claim 14 wherein: there is at least one tracking station located on the earth, said tracking station having an antenna adapted to point towards the satellite; and each deadband is chosen so that the satellite comes into view of the tracking station at substantially the same time-of-day every day of the year, and the apparent motion across the sky of the satellite with respect to the tracking station is substantially the same for every day of the year.
Claim 18
Dependent Claim
29 words
The method of claim 15 wherein the tracking station antenna tracks the satellite by means of a single programmed tracking sequence that is used every day of the year.
References Cited (Backward Citations)
US3163820A
Cited
US3243706A
Cited
US3224000A
Cited
US3349398A
Cited
US3706037A
Cited
US3836969A
Cited
US3852750A
Cited
US4004098A
Cited
US3995801A
Cited
US4375697A
Cited
US4502051A
Cited
US4630058A
Cited
US4763129A
Cited
USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1997-07-04 | 1998-01-03 | 1998-07-05 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 2001-07-04 | 2002-01-03 | 2002-07-05 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 2005-07-04 | 2006-01-03 | 2006-07-05 | $7700.00 | Window Closed / Lapsed |