| 发明名称 |
ECCENTRICITY CONTROL FOR GEOSYNCHRONOUS SATELLITES |
| 摘要 |
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. |
| 申请公布号 |
US2014339368(A1) |
申请公布日期 |
2014.11.20 |
| 申请号 |
US201414282717 |
申请日期 |
2014.05.20 |
| 申请人 |
Kratos Integral Holdings, LLC |
发明人 |
Majer Vaclav |
| 分类号 |
B64G1/24;B64G1/10 |
主分类号 |
B64G1/24 |
| 代理机构 |
|
代理人 |
|
| 主权项 |
1. A method of eccentricity control for a geosynchronous satellite, the method comprising:
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. |
| 地址 |
San Diego CA US |
