发明名称 |
Method of injecting plurality of spacecrafts into different orbits individually |
摘要 |
<p>Disclosed is a method for injecting a plurality of spacecrafts into different circum-earth or interplanetary orbits individually in a single launch. A plurality of spacecrafts coupled to an assist module are injected into an interplanetary orbit having a periodicity synchronous with the earth's revolution period. Then, in a maneuver for allowing the assist module to re-counter with and pass near to the earth (Earth swing-by), the assist module appropriately performs an orbital change maneuver and a separation maneuver for each of the spacecrafts in a sequential order. Through these maneuvers, a closest-approach point to the earth is changed for each of the spacecrafts so as to drastically change a subsequent orbital element for each of the spacecrafts. The assist module takes a sufficient time to determine a target orbit for each of the spacecrafts with a high degree of accuracy until a half month to several days before a closest-approach time in the Earth swing-by. Based on the determined orbit, the assist module makes an orbit correction of about several m/sec in a sequential order, and then separates the spacecrafts therefrom in a sequential order. In this process, an inertia navigation is performed based on an accelerometer mounted in the assist module and information about attitude.</p> |
申请公布号 |
EP1679259(A2) |
申请公布日期 |
2006.07.12 |
申请号 |
EP20060000209 |
申请日期 |
2006.01.05 |
申请人 |
KAWAGUCHI, JUNICHIRO;NEC TOSHIBA SPACE SYSTEMS, LTD. |
发明人 |
KAWAGUCHI, JUNICHIRO;KAWAKATSU, YASUHIRO;MORI, OSAMU |
分类号 |
B64G1/00;B64G1/10;B64G1/24 |
主分类号 |
B64G1/00 |
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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