发明名称 |
Argument of perigee correction with longitude control for inclined, eccentric, geosynchronous satellites |
摘要 |
A method of controlling the orbit of an inclined, eccentric geosynchronous satellite by maintaining its perigee location while simultaneously preventing a reference point on the orbit from moving too far relative to a normal position over the Earth. Doing this changes the semimajor axis of the orbit, which when perturbed away from the geosynchronous value, creates a drift rate relative to the Earth. To correct the argument of perigee and maintain the prescribed tolerance on ground track position, multiple maneuvers must be performed to control the drift rate. The relationship between maximum allowable velocity change and time between maneuvers is defined by the required correction to the argument of perigee and the allowable motion of the reference point.
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申请公布号 |
US6317661(B1) |
申请公布日期 |
2001.11.13 |
申请号 |
US20000588858 |
申请日期 |
2000.06.06 |
申请人 |
SPACE SYSTEMS/LORAL, INC. |
发明人 |
BRUNO MICHAEL J.;KEMPER BRIAN;PERVAN SHERRY |
分类号 |
B64G1/10;B64G1/24;B64G1/26;(IPC1-7):B64G1/10 |
主分类号 |
B64G1/10 |
代理机构 |
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代理人 |
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主权项 |
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地址 |
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