发明名称 CONTROL MOMENT GYRO FOR ATTITUDE CONTROL OF A SPACECRAFT
摘要 The wheel (14) rotates about an horizontal axis and is mounted on a support structure (12). The support structure has an upper web (20) which bears the wheel on one side and is integral with an inverted conical section and tubular sections of decreasing diameter (22,24,26). Angled roller bearings (18) allow electric motors (30) to rotate the support structure about the base (10)
申请公布号 KR100957240(B1) 申请公布日期 2010.05.11
申请号 KR20047014931 申请日期 2003.03.18
申请人 发明人
分类号 B64G1/28;G01C19/02;G05D1/08 主分类号 B64G1/28
代理机构 代理人
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